EP1505254B1 - Turbine à gaz et méthode pour la refroidir - Google Patents

Turbine à gaz et méthode pour la refroidir Download PDF

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Publication number
EP1505254B1
EP1505254B1 EP04103627.8A EP04103627A EP1505254B1 EP 1505254 B1 EP1505254 B1 EP 1505254B1 EP 04103627 A EP04103627 A EP 04103627A EP 1505254 B1 EP1505254 B1 EP 1505254B1
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EP
European Patent Office
Prior art keywords
steam
cooling
gas turbine
lying
guide
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
EP04103627.8A
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German (de)
English (en)
Other versions
EP1505254A2 (fr
EP1505254A3 (fr
Inventor
Dilip Mukherjee
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.)
Ansaldo Energia Switzerland AG
Original Assignee
General Electric Technology GmbH
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Publication date
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Publication of EP1505254A2 publication Critical patent/EP1505254A2/fr
Publication of EP1505254A3 publication Critical patent/EP1505254A3/fr
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Publication of EP1505254B1 publication Critical patent/EP1505254B1/fr
Not-in-force 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
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/186—Film 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
    • F05D2260/232—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 gas turbine, in particular in a power plant.
  • the invention also relates to an associated method for cooling the gas turbine.
  • Much of the electricity needed is generated in power plants using steam and / or gas turbines.
  • the efficiency of these systems is determined by the inlet temperature of the working medium (gas or steam). If higher efficiencies are to be realized, then one has to go to higher temperatures. By these temperature increases, however, the limit of the material stress is reached very quickly. Therefore, to increase the efficiency of an increased cooling of the steam and / or gas turbine is required.
  • the usual cooling medium of the hot gas-carrying components in a gas turbine is air, taken from the final or intermediate stage of the compressor.
  • Critical locations are the combustion chamber lining, the first guide blade row, the first blade row, the turbine rotor and the rear compressor section.
  • the steam cooling can be carried out as an open or closed system.
  • an open system for example, film cooling of the blades
  • the steam after it has fulfilled its cooling task, admixed with the working gas and thereby increases performance and efficiency on the gas turbine.
  • the present invention deals with the problem of providing a gas turbine of the kind mentioned an improved embodiment, with which in particular a higher performance and a longer life of the critical components can be achieved.
  • the invention is based on the general idea, in a gas turbine, which is formed with a conventional air cooling device for cooling parts of the gas turbine by means of air, in addition to provide a steam cooling device which is designed for cooling parts of the gas turbine by means of steam.
  • the cooling of a rotor and a stator of the gas turbine is conventionally carried out with air, while in addition a small amount of steam, e.g. From the inlet to the turbine to the exit from the turbine along a rotor shell parallel to the hot gas flow flows. Due to its higher heat capacity and lower viscosity, steam is in principle a better cooling medium than air. Steam instead of cooling air also reduces the required amount of cooling medium by approx. 50%.
  • the essential advantage of the invention is that the power of the additionally steam-cooled gas turbine increases compared to the conventional air-cooled gas turbine by about 2 to 5%. This results from the higher turbine inlet temperature which results in higher power. It is also noteworthy that only a comparatively small amount of steam applied in a targeted manner is needed in order to achieve intensive cooling of the gas turbine together with the air cooling.
  • the steam cooling device may be designed at least for cooling the inner inner lining and / or the inner outer lining of the combustion chamber and / or the guide vanes and / or hub-side covering elements of the vanes, and / or for a steam guide to do so is formed, that from the row of vanes along a rotor shell, a vapor film is formed.
  • This steam film protects the rotor from contact with the hot gas flow and thus leads to an extended life of the critical components of the gas turbine.
  • the steam cooling device for cooling an upstream region of the Guide vanes and the air cooling device may be formed for cooling a downstream region of the guide vanes.
  • This offers the advantage that the guide vanes are intensively cooled with steam in the thermally more heavily loaded inflow region.
  • the invention uses the knowledge that the air cooling is sufficient to cool the thermally less heavily loaded discharge area, whereby a sufficient blade cooling is achieved with relatively little energy. If the injected for cooling steam exits through outlet openings back into the hot gas stream, it creates on the outer skin of the respective vane a fine vapor layer, which lays over the vanes and this protects similar to the rotor shell in the manner described above from direct contact with the hot gas stream and thus contributes to the robustness of the gas turbine.
  • the steam required for the steam cooling device can advantageously be taken from a waste heat boiler of a steam turbine, which is coupled to the gas turbine.
  • the steam cooling thus requires no additional steam generator.
  • a gas turbine 1 according to the invention comprises a combustion chamber 2 (burner not shown), a stator 5, a rotor 8 and an air cooling device 31 only partially shown and also shown only partially steam cooling device 32.
  • the combustion chamber 2 is of an inner lining 3 and an inner outer lining 4 surrounded.
  • a hot gas stream 28 heated in the combustion chamber 2 strikes at least one row of guide vanes 6 with a plurality of guide vanes 7, which each have an inflow-side region 14 and an outflow-side region 15.
  • a blade row 9 with a plurality of blades 10, which form part of the rotor 8.
  • the steam cooling device 32 comprises a first cooling channel 24, which is arranged in the inner outer lining and is traversed by steam D during operation of the steam cooling device 32.
  • the first cooling channel 24 communicates at the end via an outer cover plate 29 with a third cooling channel 25, which is integrated in the guide blade 7.
  • the third cooling channel 25 is arranged in the inflow-side region 14 of the guide blade 7 and has Outlet openings 27, which communicate with the hot gas stream 28 on an outer side of the respective vane 7.
  • the third cooling channel 27 communicates at the end with hub-side cover elements 11, so that the remaining, not exited through the outlet openings 27 steam D flows into the hub-side cover 11 and this also cools.
  • outlet openings 27 ' are provided on the hub-side covering elements 11, from which the vapor D exits into the gas turbine 1 in the region of an inlet 21.
  • the goal here is that most of the vapor D exits through the outlet openings 27 '.
  • a second cooling channel 23 which runs essentially parallel to the hot gas stream 28 in the direction of the guide vanes 7, is arranged in the inner inner lining 3.
  • the second cooling channel 23 communicates at the end via outlet openings 27 ", which are arranged in the region of the hub-side cover elements 11, with the hot gas stream 28 at the inlet of the gas turbine 1.
  • the steam D required for the steam cooling device 32 can advantageously be taken from steam generators, not shown, in particular from a waste heat boiler, a startup steam generator or a steam turbine, which is coupled to the gas turbine. An additional steam generator for steam cooling is therefore not needed.
  • the air cooling device 31 comprises a fourth cooling channel 26 which is integrated into the guide vanes 7 in the downstream region 15.
  • the cooling channel 26 is on the input side with a cooling air source, not shown., An end or intermediate stage of a compressor, connected and output side via outlet openings 27 '' with the hot gas stream 28 and an interior of the Gas turbine 1 communicate.
  • the fourth cooling channel 26 is traversed by air L and cooled by it.
  • the blade row 9 Downstream of the guide vane row 6, the blade row 9 is arranged with a plurality of blades 10.
  • the blades 10 are cooled as in conventional gas turbines 1 with air L, which flows in the illustrated embodiment, the rotor side in the blades 10.
  • the air cooling device 31 is formed according to the illustrated embodiment, both for cooling the blades 10 and arranged downstream of the vanes 7 heat accumulators 19.
  • the cooling of the heat accumulation elements 19 takes place by cooling the side facing away from the hot gas flow 28 side of the heat accumulation elements 19.
  • Air L are injected directly downstream of the blades 10 in the gas turbine 1 and thus cause and / or enhance a cooling of the heat accumulation elements 19 on the side facing the hot gas flow 28 and the rotor shell 12.
  • the invention proposes combined cooling by means of steam D and air L.
  • the preferably slightly superheated steam D of the steam cooling device 32 flows into designated cooling channels 23 of the inner lining 3 (inner liner) and cooling channels 24 of the inner outer lining 4 (outer liner) from the burner side.
  • the inflowing steam D emerges from the end of the second cooling channel 24 and is then forwarded via a guide blade outer cover plate 29 into an adjoining third cooling channel 25.
  • the steam D flows into the hub-side cover plate 11 of the guide vane 7 and through outlet openings 27 'in the gas turbine 1.
  • the steam D flows through outlet openings 27 in the upstream region 14 of the vanes 7 in the gas turbine 1.
  • the goal here is that the majority of the steam D exits at the hub.
  • Another vapor stream D is fed to the inner liner 3 on the burner side and flows through cooling channels 23 of the inner liner 3 parallel to the hot gas flow 28 to the outlet opening 27 "in the region of the hub side cover 11.
  • the two vapor streams D of the inner liner 3 and the hub side cover plate 11 form Due to the higher density of the steam D compared to the hot gas stream 28 during the expansion along the turbine 1 downstream of the guide vanes 7 a steam curtain or film 13 of a certain current thickness along the rotor shell 12 or edge of the hot gas stream 28.
  • This steam film 13 protects the rotor eighth before contact with the hot gas stream 28 and leads thereby to an extended life of the critical components of the gas turbine.
  • the inner lining 3 and the inner outer lining 4 are cooled with steam D.
  • the amount of steam required for this is about 50% of the amount of cooling air.
  • the need for cooling slightly superheated steam D is preferably taken from a waste heat boiler, not shown. It can be provided that both the first cooling channel 24 and the second cooling channel 23 from a common or from a separate waste heat boiler (s) can be fed.
  • the power of the gas turbine 1 operated with the combined air or steam cooling increases by about 2 to 5 percent compared with the conventional air-cooled gas turbine, which can be explained as follows in a combined gas turbine steam turbine plant:
  • the steam turbine power decreases as a result of the removal slightly overheated steam D from the waste heat boiler slightly, whereas the heat output of the waste heat boiler increases as a result of the larger amount from the gas turbine. Almost the largest part of this power is therefore recovered as a result of the relaxation of the steam after cooling the inner lining 3,4 and the guide vanes 7 at a much higher temperature and up to 1 bar in the gas turbine 1.
  • the saved amount of cooling air of the guide vanes 7 flows through the combustion chamber 2 and participates in the combustion process, whereby an additional power of the gas turbine 1 is achieved.
  • the gas turbine 1 is shown in another embodiment, which is designed to carry out a sequential combustion.
  • a high-pressure combustion chamber 2 'and a Hochdruckleitschaufelschsch 42 with several high-pressure guide vanes 16 and at least one high-pressure blade row 17 is provided with a plurality of high-pressure blades 18, which are followed downstream of a low-pressure combustion chamber, not shown, and a low-pressure turbine.
  • the high pressure blades 18 and the high pressure vanes 16 are cooled at least in their Anström Jardin with steam D, while the trailing edges of the high pressure vanes 16 can be cooled either also with steam or conventional with air.
  • the design of the various cooling channels is designed so that a certain amount of steam flows through the high-pressure guide vanes 16 into the hub-side cover elements 11.
  • a large part of the steam D then flows similar to in Fig. 1 via outlet openings 27 'in the gas turbine 1 a.
  • the other part of the steam D flows into a gap 30, which is arranged below the rotor shell 12 and between the high pressure vanes 16 and the high pressure blades 18, to be sucked from there by the high pressure blades 18 for cooling.
  • a portion of the steam D blocks the described gap 30 between Hochdruckleit- and high-pressure blades 16,18 with a certain amount of blown steam D.
  • the remaining components are air-cooled.
  • FIG. 2 illustrated gas turbine 1 with sequential combustion generated by the outlet openings 27 'vapor D produced a vapor film 13 which surrounds the rotor shell 12 and protects it from direct contact with the hot gas stream 28.
  • Fig. 3 an embodiment variant for cooling a high-pressure compressor 20 is shown.
  • suitable heat accumulation elements 19 are arranged between the high-pressure guide vanes 16 and the high-pressure blades 18 on the rotor shell 12 and with slightly superheated steam D, which at Fed to the end of the high pressure compressor 20 and after a certain distance at the end of the high pressure compressor 20 is returned, cooled.
  • the cooling of the rotor 8 and the stator 5 is carried out conventionally with air L.
  • air L now flows a small amount of steam from the inlet 21 into the gas turbine 1 to the exit from the gas turbine 1 along the rotor shell 12 parallel to the hot gas stream 28. Due to the higher density of the vapor D compared to the hot gas stream 28 thereby remains a vapor film 13 on the rotor shell 12 and protects it from direct contact with the hot gas stream 28.
  • the advantages of the invention are that the power of the additionally cooled with steam D gas turbine 1 compared to the conventional air-cooled gas turbine 1, for example by about 2 to 5%, increases and at the same time due to the vapor film 13 a longer life of the critical components can be achieved ,

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

Claims (14)

  1. Turbine à gaz (1), plus particulièrement dans une centrale,
    - avec au moins une chambre de combustion (2) et un carénage interne (3) entourant la chambre de combustion (2) et avec un carénage externe (4),
    - avec un stator (5), qui comprend au moins une série d'aubes directrices (6) avec plusieurs aubes directrices (7),
    - avec un rotor (8), qui comprend au moins une série d'aubes directrices (9) avec plusieurs aubes directrices (10),
    - avec un dispositif de refroidissement par air (31) qui est conçu pour le refroidissement de parties de la turbine à gaz (1) avec de l'air (L),
    - un dispositif de refroidissement par vapeur (32) étant en outre prévu, qui permet le refroidissement des aubes directrices (7) et/ou des éléments de recouvrement côté moyeu (11) des aubes directrices (7) avec de la vapeur (D),
    caractérisée en ce que
    - le dispositif de refroidissement par vapeur (32) est conçu pour le refroidissement du carénage interne (3) et/ou du carénage externe (4) et en ce qu'un guidage de vapeur est conçu de façon à ce qu'un film de vapeur (13) se forme à partie de la série d'aubes directrices (6) le long d'une enveloppe du rotor (12).
  2. Turbine à gaz selon la revendication 1, caractérisée en ce que, dans le carénage externe (4), un deuxième canal de refroidissement (24) est conçu de façon à ce qu'une plaque de recouvrement externe d'aube directrice (29) transmette la vapeur sortant du deuxième canal de refroidissement (24) vers un troisième canal de refroidissement (25).
  3. Turbine à gaz selon la revendication 1 ou 2, caractérisée en ce que, dans le carénage externe (3), un premier canal de refroidissement (23) est conçu de façon à ce qu'une ouverture de sortie (27") du premier canal de refroidissement (23) est disposée au niveau d'éléments de recouvrement côté moyeu (11) des aubes directrices (7).
  4. Turbine à gaz selon l'une des revendications précédentes, caractérisée en ce que les aubes directrices (7) comprennent des ouvertures de sortie et en ce que les ouvertures de sortie conduisent la vapeur soufflée dans le flux de gaz chaud.
  5. Turbine à gaz selon l'une des revendications précédentes, caractérisée en ce que le dispositif de refroidissement par air (31) est conçu au moins pour le refroidissement des aubes directrices (10) et/ou d'éléments d'accumulation thermique (19) disposés en aval de la série d'aubes directrices (6).
  6. Turbine à gaz selon l'une des revendications précédentes, caractérisée en ce que le dispositif de refroidissement par vapeur (32) est conçu pour le refroidissement des aubes directrices (7) dans une zone côté entrée (14) et le dispositif de refroidissement par air (31) est conçu pour le refroidissement des aubes directrices (7) dans une zone côté sortie (15).
  7. Turbine à gaz selon l'une des revendications précédentes, caractérisée en ce que
    - la turbine à gaz (1) est conçue pour la réalisation d'une combustion séquentielle,
    - une chambre de combustion à haute pression (2') est en outre prévue, qui est munie d'un carénage interne (3) entourant celle-ci et d'un carénage externe (4),
    - au moins une série d'aubes directrices haute pression (22) avec plusieurs aubes directrices haute pression (16) est prévue,
    - au moins une série d'aubes directrices haute pression (17) avec plusieurs aubes directrices haute pression (18) est prévue.
  8. Turbine à gaz selon la revendication 7, caractérisée en ce que
    - le dispositif de refroidissement par vapeur (32) est conçu au moins pour le refroidissement des aubes directrices haute pression (16) et/ou d'éléments de recouvrement côté moyeu (11) des aubes directrices haute pression (16) et/ou des aubes directrices haute pression (18) et/ou
    - un guidage de vapeur est conçu de façon à ce que, à partir de la série d'aubes directrices haute pression (22), un film de vapeur (13) apparaît le long d'une enveloppe de rotor (12).
  9. Turbine à gaz selon la revendication 7 ou 8, caractérisée en ce que le dispositif de refroidissement par vapeur (31) est conçu au moins pour le refroidissement du carénage interne (3) de la chambre de combustion haute pression (2') et/ou du carénage externe (4) de la chambre de combustion haute pression (2') et/ou de l'arête arrière des aubes directrices haute pression (16) et/ou d'éléments d'accumulation thermique (19) disposés en aval de la série d'aubes directrices haute pression (22).
  10. Turbine à gaz selon l'une des revendications 7 à 9, caractérisée en ce que le dispositif de refroidissement par vapeur (32) est conçu au moins pour le refroidissement partiel d'un compresseur haute pression (20).
  11. Turbine à gaz selon l'une des revendications 7 à 10, caractérisée en ce que le dispositif de refroidissement par vapeur (32) est relié, pour le prélèvement de vapeur (D), avec une chaudière de récupération d'une turbine à vapeur couplée avec la turbine à gaz (1).
  12. Procédé de refroidissement d'une turbine à gaz (1), plus particulièrement dans une centrale, comprenant :
    - une chambre de combustion (2), avec un carénage interne (3) entourant la chambre de combustion (2) et avec un carénage externe (4),
    - un stator (5), qui comprend au moins une série d'aubes directrices (6) avec plusieurs aubes directrices (7),
    - un rotor (8), qui comprend au moins une série d'aubes directrices (9) avec plusieurs aubes directrices (10),
    - dans lequel des parties de la turbine à gaz (1) sont refroidies au moyen d'un dispositif de refroidissement par air (31) avec de l'air (L) tandis que les aubes directrices (7) et/ou les éléments de recouvrement côté moyeu (11) des aubes directrices (7) sont refroidies au moyen d'un dispositif de refroidissement par vapeur (32) avec de la vapeur (D),
    caractérisé en ce qu'un guidage de vapeur permet de générer, à partir de la série d'aubes directrices (6), un film de vapeur le long d'une enveloppe de rotor (12) et le dispositif de refroidissement par vapeur (32) refroidit le carénage interne (3) et/ou le carénage externe (4).
  13. Procédé selon la revendication 12, caractérisé par les caractéristiques d'au moins une des revendications 2 à 9.
  14. Procédé selon la revendication 12 ou 13, caractérisé en ce que la vapeur soufflée pour le refroidissement des aubes directrices (7) sort par des ouvertures de sortie dans le flux de gaz chaud et génère un film de vapeur au niveau de l'enveloppe externe des aubes directrices (7) respectives.
EP04103627.8A 2003-08-08 2004-07-28 Turbine à gaz et méthode pour la refroidir Not-in-force EP1505254B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10336432 2003-08-08
DE10336432A DE10336432A1 (de) 2003-08-08 2003-08-08 Gasturbine und zugehöriges Kühlverfahren

Publications (3)

Publication Number Publication Date
EP1505254A2 EP1505254A2 (fr) 2005-02-09
EP1505254A3 EP1505254A3 (fr) 2012-07-04
EP1505254B1 true EP1505254B1 (fr) 2017-01-25

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EP04103627.8A Not-in-force EP1505254B1 (fr) 2003-08-08 2004-07-28 Turbine à gaz et méthode pour la refroidir

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US (1) US7040097B2 (fr)
EP (1) EP1505254B1 (fr)
CN (1) CN100507237C (fr)
DE (1) DE10336432A1 (fr)

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CN1580520A (zh) 2005-02-16
DE10336432A1 (de) 2005-03-10
EP1505254A2 (fr) 2005-02-09
CN100507237C (zh) 2009-07-01
US7040097B2 (en) 2006-05-09
US20050172634A1 (en) 2005-08-11
EP1505254A3 (fr) 2012-07-04

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