EP1536102B1 - Rotor pour une turbine à vapeur - Google Patents

Rotor pour une turbine à vapeur Download PDF

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Publication number
EP1536102B1
EP1536102B1 EP04105832.2A EP04105832A EP1536102B1 EP 1536102 B1 EP1536102 B1 EP 1536102B1 EP 04105832 A EP04105832 A EP 04105832A EP 1536102 B1 EP1536102 B1 EP 1536102B1
Authority
EP
European Patent Office
Prior art keywords
rotor
channel
cooling
well
inflow
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.)
Not-in-force
Application number
EP04105832.2A
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German (de)
English (en)
Other versions
EP1536102A2 (fr
EP1536102A3 (fr
Inventor
Michael Dr. Hiegemann
Martin Reigl
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.)
General Electric Technology GmbH
Original Assignee
General Electric Technology GmbH
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
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Publication of EP1536102A2 publication Critical patent/EP1536102A2/fr
Publication of EP1536102A3 publication Critical patent/EP1536102A3/fr
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Publication of EP1536102B1 publication Critical patent/EP1536102B1/fr
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Anticipated expiration legal-status Critical

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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
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/085—Heating, heat-insulating or cooling means cooling fluid circulating inside the rotor
    • 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
    • F01D5/063—Welded rotors
    • 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
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/085—Heating, heat-insulating or cooling means cooling fluid circulating inside the rotor
    • F01D5/087—Heating, heat-insulating or cooling means cooling fluid circulating inside the rotor in the radial passages of the rotor disc
    • 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
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/085—Heating, heat-insulating or cooling means cooling fluid circulating inside the rotor
    • F01D5/088—Heating, heat-insulating or cooling means cooling fluid circulating inside the rotor in a closed cavity
    • 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
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • 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
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/205—Cooling fluid recirculation, i.e. after cooling one or more components is the cooling fluid recovered and used elsewhere for other purposes
    • 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
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/232—Heat transfer, e.g. cooling characterized by the cooling medium
    • F05D2260/2322—Heat transfer, e.g. cooling characterized by the cooling medium steam

Definitions

  • the present invention relates to a rotor for a steam turbine for working steam, having the features of the preamble of claim 1.
  • Such a rotor for a steam turbine is for example from the EP 0 991 850 B1 known and extends along an axis of rotation and consists of at least two adjacent rotor parts in the axial direction.
  • the two rotor parts are welded together at mutually facing axial end faces by means of a circumferentially closed circumferential, annular weld zone.
  • a cooling channel system is formed which has at least one inflow channel, at least one outflow channel and a cooling channel.
  • the cooling channel leads cooling steam from at least one inflow channel to the at least one outflow channel.
  • the at least one inflow channel removes the cooling steam at a position on the rotor surface of the working steam and supplies it to the cooling channel.
  • the at least one outflow channel removes the cooling steam from the cooling channel and leads it to or through a cooling zone of the rotor.
  • a suitable Positioning of the at least one inflow channel and the at least one outflow channel can be formed between and inlet and outlet of the cooling channel system, a pressure difference sufficient to promote the cooling steam without additional measures from the at least one vapor extraction point to the at least one cooling zone.
  • the cooling channel extends concentrically to the axis of rotation.
  • the inflow channels are arranged in the region of a diffuser of a high-pressure single-flow turbine, while the outflow channels are positioned in the center of a double-flow medium-pressure turbine.
  • the cooling channel extends within the common rotor provided for the high-pressure turbine and the medium-pressure turbine.
  • This rotor is mounted axially between high-pressure turbine and medium-pressure turbine. Accordingly, the cooling line extends centrally through this camp. As a result of this camp is exposed to increased temperature stress, so that additional measures to protect this camp are required.
  • the known rotor is realized according to a so-called "drum construction", that is, the rotor is composed of a plurality of "drums".
  • a drum is a cylindrical or frusto-conical solid body which may generally contain voids, such as channels and chambers, of a cooling system.
  • a rotor with a drum construction is usually characterized by a small number of drums, which are preferably designed differently. Each drum is assigned to several turbine stages. Adjacent drums are frontally usually on the entire surface to each other.
  • the US 6048169 A describes a turbine shaft of a steam turbine having shaft segments having connection openings and two axially spaced passages, which are connected to an axial gap and a cavity, for flowing through a cooling medium.
  • a one-piece rotor which is arranged in a double-flow steam turbine and also contains a cooling channel system.
  • a cavity is formed in the center of the hot steam supply to the jacket, which is closed again by means of a lid, wherein the lid simultaneously fulfills a Strömungsleitfunktion. From this cavity is on each of two axially opposite sides of an axial cooling channel.
  • the one cooling channel communicates with an inflow channel, which takes the cooling steam of a pressure stage of a flood.
  • the other cooling channel communicates with a discharge channel, which supplies the cooling steam of a pressure stage of the other flood.
  • a rotor for a gas turbine on which a compressor part, a central part and a turbine part are formed and which consists mainly of individual, welded together rotational bodies whose geometric shape leads to the formation of axially symmetric cavities between the respective adjacent bodies of revolution.
  • a further extending around the central axis of the rotor, ranging from the downstream end of the rotor to the upstream last cavity further, cylindrical cavity and at least two tubes provided, which have different diameters and lengths and at least partially overlap telescopically and which are arranged in the cylindrical cavity.
  • the tubes are each firmly anchored to a fixed point, wherein the fixed points of the tubes are at axially different locations.
  • the tubes are each provided with at least two passage openings in the jacket, wherein at least one opening in the turbine part and at least one opening in the compressor or central part is arranged.
  • the openings of the various tubes overlap in the operating state in the turbine part and in the cold state in the compressor and central part. In this way, when the turbine is started up, the rotor can be warmed up faster, while cooling is provided in the operating state.
  • compressed air is taken from a suitable compressor stage and fed axially to one of the tubes.
  • This known rotor is realized with the so-called “disk construction", ie, the rotor is assembled from several “slices".
  • the discs correspond to disc-shaped bodies, which have radially outwardly an axially projecting edge region, which may be designed in the manner of a sleeve.
  • the adjacent discs abut each other at the edge regions along relatively small annular surfaces.
  • These discs are thus the aforementioned rotating body.
  • Each disc is in contrast to a drum only a few, in each case associated with only a single turbine stage.
  • a disk-type rotor consists of a comparatively large number of disks, which are also preferably of identical construction.
  • the cavities realized in a rotor with a disk construction serve primarily to reduce the inertial forces, but can additionally be used for a cooling system.
  • Further rotors for gas turbines which are realized in this disc construction, can, for example, from DE 854 445 B , the DE 198 52 604 A1 and the DE 196 17 539 A1 be removed.
  • the present invention deals with the problem of providing for a rotor of a steam turbine of the type mentioned in an improved embodiment which, in particular at reduced production costs sufficient cooling of the respective cooling zone of the rotor, in particular the rotor interior, allows.
  • the invention is based on the general idea, in a rotor whose rotor parts for producing the welded connection each have an indentation on the front side, which together form a cavity enclosed by the welding zone in the welded state, these in the production of the rotor anyway existing cavity in the cooling channel system integrate.
  • the cavity or the depressions mentioned can be used before the welding of the rotor parts to introduce the cooling channel (s) and / or the inflow channel (s) and / or the outflow channel (s) into the respective rotor part. Additional recesses, which on the one hand lead to a material weakening and on the other hand have to be closed again, are therefore unnecessary.
  • the effort to realize the rotor internal cooling channel system can be reduced. simultaneously the cavity receives a meaningful double function, whereby the overall relative expense of forming the welded connection or the rotor relativized.
  • the steam turbine is designed to be single-flow and the at least one cooling zone comprises a thrust balance piston of the rotor.
  • the cooling effect of a cooling steam flow through bore system is particularly large when many small holes are used as cooling channels instead of a large bore, because then the cooling duct wall acted upon by the cooling steam is considerably larger.
  • the cross-sectional area of a cooling channel should be small so that a high velocity of the cooling steam is achieved and thus the heat transfer, ie the cooling effect, is improved.
  • the many cooling channels do not run in the rotor center, since a piercing of the rotor center considerably weakens the strength of the rotor there.
  • the mechanical stress in the rotor center due to the rotor centrifugal force is of particular importance. It often represents a limit of the buildable.
  • a rotor which is made of at least three rotor parts and accordingly comprises two welding zones and two cavities.
  • the two cavities can then pass through at least one Cooling channel be connected to each other, while the at least one inflow channel terminates at the one cavity and the at least one outflow channel begins at the other cavity.
  • the cavities form quasi node points which establish the communication between the at least one cooling channel and the at least one inflow channel on the one hand and the at least one outflow channel on the other hand.
  • a steam turbine 1 comprises a rotor 2, which is rotatably mounted at its axial ends 3 and 4 about a central axis of rotation 5.
  • the rotor 2 is arranged centrally in a housing 6 which carries a plurality of guide vanes 7.
  • the rotor 2 carries a plurality of rotor blades 8, the rotor blades 8 and the stator blades 7 forming in pairs the turbine stages 9 of the steam turbine 1.
  • a steam turbine 1 works with steam as a working medium, also called working steam.
  • the housing 6 contains an inflow space 10 to which the tensioned steam is supplied and from which the steam is led to the first turbine stage 9 of the steam turbine 1.
  • the expanded steam is discharged at an outlet 11 of the housing 6.
  • Arrows 12 symbolize the main flow of the steam through the steam turbine 1.
  • the rotor 2 is designed in several parts and has in the embodiments of Fig. 1 to 5 two rotor parts 2a and 2b, which adjoin each other in the axial direction.
  • the rotor 2 is designed here as a "drum rotor” 2, ie, the rotor 2 is realized according to the drum design.
  • the individual rotor parts 2a, 2b form the "drums" of the drum rotor 2. They are characterized by their massive design with large material thickness in the radial and axial directions.
  • the two rotor parts 2a, 2b are welded together.
  • a welding zone 15 is formed on mutually facing axial end faces 13 and 14 of the rotor parts 2a, 2b, which extends in the circumferential direction and thereby rotates closed. In this way, the welding zone 15 is given an annular shape.
  • the two rotor parts 2a, 2b are provided at their end faces 13, 14 each with a recess 16 or 17 of any shape.
  • the two depressions 16, 17 complement one another to form a cavity 18.
  • This cavity 18 is thus surrounded circumferentially by the welding zone 15.
  • the rotor 2 is also equipped with an internal cooling channel system 19, which makes it possible to remove partially relaxed and thus partially cooled vapor at a position on the rotor surface 20 and this as cooling steam at least one thermally loaded component of the rotor 2, such. B. a thrust balance piston 21 supply.
  • the cooling steam is the same medium as the working steam.
  • the cooling channel system 19 comprises at least one inflow channel 22 for removing the cooling steam from the working steam at a position on the rotor surface 20 at a turbine stage 9 suitable for this purpose. In the present case, two such inflow channels 22 are shown. It is clear that too more than two inflow channels 22 may be provided, which may be arranged in particular star-shaped with respect to the axis of rotation 5.
  • At least one outflow channel 23 is provided which guides the cooling steam through at least one cooling zone, here exemplarily the thrust balance piston 21 and / or to a cooling zone of the rotor 2 or a rotor or turbine component.
  • at least one cooling zone here exemplarily the thrust balance piston 21 and / or to a cooling zone of the rotor 2 or a rotor or turbine component.
  • two outflow channels 23 are also shown.
  • more than two outflow channels 23 may be provided, which may be arranged in particular star-shaped with respect to the axis of rotation 5.
  • the cooling channel system 19 comprises at least one cooling channel 24, which together or in each case connect the at least one inflow channel 22 to the at least one outflow channel 23.
  • the cooling steam is removed according to the arrows 25 via the at least one inflow channel 22 of the respective turbine stage 9, supplied via the or the cooling channels 24 to at least one outflow channel 23, which in turn the cooling steam of the respective cooling zone, for. B. the thrust balance piston 21, supplies. Due to the selected positioning of the inflow ends of the inflow channels 22 and the outflow ends of the outflow channels 23, there is a pressure gradient within the cooling channel system 19, which automatically transports the cooling steam within the cooling channel system 19 in the desired manner.
  • the cavity 18 is now integrated into the cooling channel system 19.
  • the cooling channels 24 are each connected to this cavity 18.
  • the cooling channel 24 shown on the right is connected on the input side to the inflow channels 22 and the output side to the cavity 18.
  • the cooling channel 24 shown on the left is connected to the input side of the cavity 18 and In this way, the cavity 18 to a flowed through by the cooling steam component of the cooling channel system 19.
  • the cavity 18 forms a kind of distribution node, the cooling steam, which is supplied via one or more channels 22 or 24, to a or multiple channels 23, 24 distributed.
  • the two cooling channels 24 are each designed centric to the axis of rotation 5 in the respective rotor part 2a, 2b.
  • the design of these cooling channels 24 is particularly simple, since the rotor parts 2a, 2b can be drilled centrally before welding in the region of their recesses 16, 17 in order to form these cooling channels 24.
  • An additional, alternatively mounted recess in the surface of the respective rotor part 2a, 2b is not required.
  • the inflow channels 22, which extend essentially radially here, can be produced in the form of bores. The same applies to the discharge channels 23, which extend here diagonally - centrally. With regard to the flow direction within the cooling channel system 19, the cooling channel 24 shown on the right ends on the cavity 18, while the cooling channel 24 shown on the left begins at the cavity 18.
  • FIG. 2 The embodiment shown differs from that in FIG Fig. 1 shown embodiment in that in the rotor part shown on the right 2a no central cooling channel 24, but a plurality of decentralized or with respect to the rotation axis 5 eccentrically arranged, but parallel to the longitudinal axis extending cooling channels 24 are provided, each communicate with one of the inflow channels 22. In this construction, the attachment of a central cooling channel 24 can be avoided, which may be advantageous in certain rotor designs.
  • the number of cooling channels 24 formed in the right-hand rotor part 2a then corresponds to the number of inflow channels 22 provided there.
  • a plurality of fan-like arranged inflow channels 22 may encounter a cooling channel 24.
  • the embodiment of the Fig. 3 differs from the embodiment according to Fig. 2 in that, in addition to a central cooling channel 24, a plurality of decentralized or with respect to the rotation axis 5 eccentrically arranged cooling channels 24 are provided in the rotor part 2b shown on the left. These cooling channels 24 also preferably extend parallel to the longitudinal axis of the rotor 2 and in each case communicate with one of the outflow channels 23. The number of cooling channels 24 in the rotor part 2b shown on the left then corresponds to the number of outflow channels 23 attached thereto, although this does not necessarily have to be. In the case of certain embodiments of the rotor 2, the attachment of a plurality of decentralized or eccentric cooling channels 24 with respect to a central cooling channel 24 can also be advantageous in the case of the left rotor part 2b.
  • cooling channels 24 extend parallel to each other eccentrically, as for example in the embodiments of Fig. 2 and 3 is the case, these are expediently symmetrically distributed in the respective rotor part 2a, 2b arranged, that is, the respective cooling channels 24 are arranged concentrically around the rotation axis 5 around.
  • the cavity 18 is arranged quasi between the successive cooling channels 24 in the axial direction.
  • the inflow channels 22 and the outflow channels 23 can communicate with the cavity 18 only via the cooling channels 24.
  • the pitch of the rotor 2 adapted to the position of the outflow channels 23, that is, the welding zone 15 is compared to the embodiments of the Fig. 1 to 3 in the direction of the respective cooling zone, ie shifted here in the direction of the thrust balance piston 21.
  • the cooling passage system 19 is as in the embodiment according to FIG Fig. 1 designed by a central cooling channel 24 is provided, which communicates with the inflow channels 22.
  • FIG. 5 The embodiment shown differs from the embodiment according to FIG Fig. 4 in that a plurality of decentralized or eccentrically arranged to the rotation axis 5 cooling channels 24 are provided in the right rotor part 2a instead of the central cooling channel 24, each communicating with one of the inflow channels 22. This may be advantageous for certain embodiments of the rotor 2.
  • the outflow channels 23 are connected directly to the cavity 18, while the inflow channels 22 are connected indirectly via the cooling channels 24 to the cavity 18.
  • the pitch of the rotor 2 is selected such that the inflow channels 22 can be connected directly to the cavity 18, while the outflow channels 23 are then connected indirectly via one or more cooling channels 24 to the cavity 18 could be.
  • the welding zone 15 is then displaced in the direction of the removal point of the cooling steam.
  • the at least one cooling channel 24 may be formed by the cavity 18, with the result that both the inflow channels 22 and the outflow channels 23 are connected directly to the cavity 18.
  • the at least one removal points here the respective turbine stage 9
  • the at least one cooling zone here the thrust balance piston 21
  • the at least one inflow channel 22 is necessarily arranged in the one rotor part 2a
  • the at least one outflow channel 23 is arranged in the other rotor part 2b.
  • the cooling channel system 19 thus extends within the two-piece rotor 2 through both rotor parts 2a and 2b.
  • Fig. 6 an embodiment with a three-part rotor 2, wherein the individual rotor parts are designated from right to left with 2a, 2b and 2c.
  • This rotor 2 is designed as a drum rotor 2. Due to the three-parted two welding zones 15 and thus two cavities 18 are accordingly provided. In this case, both cavities 18 are integrated into the cooling channel system 19 in the sense of the invention.
  • the pitch of the rotor 2 is specifically chosen so that the inflow channels 22 communicate directly with the one cavity 18, while the outflow channels 23 communicate directly with the other cavity 18.
  • the two cavities 18 are then connected to one another via the at least one cooling channel 24, here via at least two cooling channels 24.
  • This targeted division of the rotor 2 simplifies the integration of the cooling channel system 19 into the rotor 2.
  • simple bores can be provided which are from the respective removal point or lead from the respective cooling zone to the respective cavity 18.
  • the one or more cooling channels 24 can be prepared by simple holes.
  • only the inflow channels 22 and in the rotor part 2c shown on the left are exclusively the outflow channels 23 formed, while the central rotor part 2b contains only the or the cooling channels 24.
  • two or more cooling channels 24 are arranged eccentrically in the central rotor part 2b.
  • a central cooling channel 24 extends between the two cavities 18.
  • at least one of the welding zones 15 is positioned so that the associated outer rotor part 2 a or 2 c contains neither an inflow channel 22 nor an outflow channel 23.
  • the welding zone 15 shown on the right can be positioned to the right of the cooling steam removal point, with the result that the inflow passages 22 then have to be formed in the central rotor part 2b.
  • This design leads to the fact that in the right rotor part 2a then no inflow channel 22 is included.
  • twin-flow steam turbines 1 While in the embodiments of Fig. 1 to 6 the steam turbine 1 is designed single-flow, show the Fig. 7 to 9 twin-flow steam turbines 1.
  • the two floods are designated 26 and 27 respectively.
  • the rotor 2 In this twin-flow steam turbine 1, the rotor 2 is again in three parts and formed as a drum rotor 2, wherein the central rotor part 2b hineinerstreckt in both floods 26, 27.
  • the division of the rotor 2 is targeted so that the welding zones 15 are each positioned with their cavities 18 so that the Inflow channels 22 directly to the one, here to the left cavity 18, and the outflow channels 23 directly to the other, here to the right cavity 18, can be connected.
  • the two cavities 18 then communicate with each other via the at least one cooling channel 24.
  • cooling steam of the flood 27 shown on the left can be taken at a certain turbine stage 9 and the blading 26 are shown the other flood 26 shown on the right.
  • a sufficient pressure gradient arises within the cooling channel system 19 in order to be able to drive the cooling steam without additional measures.
  • the two cavities 18 are interconnected by a centrally disposed cooling channel 24.
  • the two cavities 18 are interconnected by two or more cooling channels 24 arranged eccentrically with respect to the axis of rotation 5.
  • these cooling channels 24 are arranged concentrically distributed about the rotation axis 5. In this case, the number of cooling channels 24 does not have to match either the number of inflow channels 22 or the number of outflow channels 23.
  • Fig. 7 and 8th are the inflow channels 22 in the rotor part 2c shown on the left, the outflow channels 23 in the rotor part 2a shown on the right and the one or more cooling channels 24 formed in the central rotor part 2b.
  • Fig. 9 shows an embodiment which is not part of the invention, in which both the inflow channels 22 and the outflow channels 23 are arranged in the central rotor part 2b, in which the cooling channels or the channels 24 are formed. In this construction, therefore, only the central rotor part 2 b must be processed in order to form the cooling channel system 19 in the entire rotor 2. The cost of implementing the cooling channel system 19 is thereby reduced.

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

Claims (11)

  1. Rotor pour une turbine à vapeur (1) pour de la vapeur de travail,
    - dans lequel la turbine à vapeur (1) est réalisée à un seul flux,
    - dans lequel le rotor (2) s'étend le long d'un axe de rotation (5) et se compose d'au moins deux parties de rotor (2a, 2b, 2c) contiguës les unes aux autres dans la direction axiale,
    - dans lequel deux parties de rotor (2a, 2b, 2c) sont soudées respectivement l'une à l'autre sur des côtés avant (13, 14) axiaux tournés l'un vers l'autre au moyen d'une zone de soudage (15) annulaire périphérique de manière fermée dans la direction périphérique,
    - dans lequel un système de canal de refroidissement (19) est réalisé dans le rotor (2), lequel présente au moins un canal d'afflux (22), au moins un canal d'écoulement (23) et au moins un canal de refroidissement (24) s'étendant axialement dans le rotor (2),
    - dans lequel l'au moins un canal de refroidissement (24) achemine de la vapeur de refroidissement directement ou indirectement de l'au moins un canal d'afflux (22) directement ou indirectement vers l'au moins un canal d'écoulement (23),
    - dans lequel l'au moins un canal d'afflux (22) retire la vapeur de refroidissement à une position à la surface de rotor (20) de la vapeur de travail,
    - dans lequel l'au moins un canal d'écoulement (23) achemine la vapeur de refroidissement par au moins une et/ou vers au moins une zone de refroidissement,
    - dans lequel l'au moins une zone de refroidissement comporte un piston de compensation de poussée (21) du rotor (2),
    - dans lequel, au moins pour deux parties de rotor (2a, 2b, 2c), la zone de soudage (15) entoure une cavité (18) sur la périphérie qui est formée de deux évidements (16, 17) qui sont introduits respectivement dans la partie de rotor (2a, 2b, 2c) associée côté avant,
    - dans lequel l'au moins une cavité (18) forme une partie du système de canal de refroidissement (19) et est parcourue par la vapeur de refroidissement.
  2. Rotor selon la revendication 1,
    caractérisé en ce
    - qu'au moins un canal de refroidissement (24) communiquant avec au moins un canal d'afflux (22) se termine au niveau de l'au moins une cavité (18),
    - qu'au moins un canal de refroidissement (24) communiquant avec au moins un canal d'écoulement (23) commence au niveau de l'au moins une cavité (18).
  3. Rotor selon la revendication 1,
    caractérisé en ce
    - qu'au moins un canal de refroidissement (24) communiquant avec au moins un canal d'afflux (22) se termine au niveau de l'au moins une cavité (18),
    - que l'au moins un canal d'écoulement (23) commence au niveau de cette cavité (18).
  4. Rotor selon la revendication 1,
    caractérisé en ce
    - qu'au moins un canal de refroidissement (24) communiquant avec au moins un canal d'écoulement (23) commence au niveau de la cavité (18),
    - que l'au moins un canal d'afflux (22) se termine au niveau de cette cavité (18).
  5. Rotor selon la revendication 1,
    caractérisé en ce
    - que l'au moins un canal de refroidissement (24) est formé par la cavité (18),
    - que l'au moins un canal d'afflux (22) se termine au niveau de la cavité (18),
    - que l'au moins un canal d'écoulement (23) commence au niveau de la cavité (18).
  6. Rotor selon l'une quelconque des revendications 1 à 5,
    caractérisé en ce
    - que l'au moins un canal d'afflux (22) s'étend dans l'une partie de rotor (2a) alors que l'au moins un canal d'écoulement (23) s'étend dans l'autre partie de rotor (2b).
  7. Rotor selon la revendication 1,
    caractérisé en ce
    - que, pour un rotor (1) avec au moins trois parties de rotor (2a, 2b, 2c), deux zones de soudage (15) et deux cavités (18) sont prévues,
    - que les deux cavités (18) sont raccordées l'une à l'autre par l'au moins un canal de refroidissement (24),
    - que l'au moins un canal d'afflux (22) se termine au niveau de l'une cavité (18),
    - que l'au moins un canal d'écoulement (23) commence au niveau de l'autre cavité (18).
  8. Rotor selon la revendication 7,
    caractérisé en ce
    - que l'au moins un canal d'afflux (22) s'étend dans l'une partie de rotor (2c) extérieure ou dans la partie de rotor (2b) médiane des trois parties de rotor (2a, 2b, 2c),
    - que l'au moins un canal d'écoulement (23) s'étend dans l'autre partie de rotor (2a) extérieure ou dans la partie de rotor (2b) médiane des deux parties de rotor (2a, 2b, 2c).
  9. Rotor selon l'une quelconque des revendications 1 à 8,
    caractérisé en ce
    - que l'au moins un canal de refroidissement (24) s'étend concentriquement à l'axe de rotation (5), ou
    - que l'au moins un canal de refroidissement (24) s'étend de manière excentrée à l'axe de rotation (5) et sensiblement parallèlement à celui-ci.
  10. Rotor selon l'une quelconque des revendications 1 à 9,
    caractérisé en ce
    - que l'au moins un canal d'afflux (22) s'étend par rapport à l'axe de rotation (5) sensiblement radialement ou de manière diagonale et centrée ou diagonale et décentrée de telle manière qu'il atteigne le canal de refroidissement (24), et/ou
    - que l'au moins un canal d'écoulement (23) s'étend par rapport à l'axe de rotation (5) sensiblement radialement ou de manière diagonale et centrée ou diagonale et décentrée de telle manière qu'il atteigne le canal de refroidissement (24).
  11. Rotor selon l'une quelconque des revendications 1 à 10,
    caractérisé en ce
    que le rotor (2) est constitué, selon le type de tambour en tant que rotor à tambour (2), de plusieurs tambours formés par les parties de rotor (2a, 2b, 2c).
EP04105832.2A 2003-11-28 2004-11-17 Rotor pour une turbine à vapeur Not-in-force EP1536102B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10355738 2003-11-28
DE10355738A DE10355738A1 (de) 2003-11-28 2003-11-28 Rotor für eine Turbine

Publications (3)

Publication Number Publication Date
EP1536102A2 EP1536102A2 (fr) 2005-06-01
EP1536102A3 EP1536102A3 (fr) 2012-08-22
EP1536102B1 true EP1536102B1 (fr) 2019-03-20

Family

ID=34442341

Family Applications (1)

Application Number Title Priority Date Filing Date
EP04105832.2A Not-in-force EP1536102B1 (fr) 2003-11-28 2004-11-17 Rotor pour une turbine à vapeur

Country Status (3)

Country Link
US (1) US7267525B2 (fr)
EP (1) EP1536102B1 (fr)
DE (1) DE10355738A1 (fr)

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JP5049578B2 (ja) 2006-12-15 2012-10-17 株式会社東芝 蒸気タービン
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US8105032B2 (en) * 2008-02-04 2012-01-31 General Electric Company Systems and methods for internally cooling a wheel of a steam turbine
US8484975B2 (en) * 2008-02-05 2013-07-16 General Electric Company Apparatus and method for start-up of a power plant
EP2211017A1 (fr) * 2009-01-27 2010-07-28 Siemens Aktiengesellschaft Rotor doté d'un espace creux pour une turbomachine
US8453463B2 (en) * 2009-05-27 2013-06-04 Pratt & Whitney Canada Corp. Anti-vortex device for a gas turbine engine compressor
US8251643B2 (en) * 2009-09-23 2012-08-28 General Electric Company Steam turbine having rotor with cavities
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JP7242597B2 (ja) * 2020-03-12 2023-03-20 東芝エネルギーシステムズ株式会社 タービンロータ
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Also Published As

Publication number Publication date
EP1536102A2 (fr) 2005-06-01
US7267525B2 (en) 2007-09-11
DE10355738A1 (de) 2005-06-16
US20050118025A1 (en) 2005-06-02
EP1536102A3 (fr) 2012-08-22

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