EP1788191A1 - Turbine à vapeur et procédé pour le refroidissement d'une turbine à vapeur - Google Patents

Turbine à vapeur et procédé pour le refroidissement d'une turbine à vapeur Download PDF

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Publication number
EP1788191A1
EP1788191A1 EP05025245A EP05025245A EP1788191A1 EP 1788191 A1 EP1788191 A1 EP 1788191A1 EP 05025245 A EP05025245 A EP 05025245A EP 05025245 A EP05025245 A EP 05025245A EP 1788191 A1 EP1788191 A1 EP 1788191A1
Authority
EP
European Patent Office
Prior art keywords
turbine
pressure turbine
medium
steam
pressure
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
EP05025245A
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German (de)
English (en)
Other versions
EP1788191B1 (fr
Inventor
Frank Dr. Deidewig
Norbert Pieper
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Siemens AG
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Siemens AG
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Publication date
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Priority to EP20050025245 priority Critical patent/EP1788191B1/fr
Publication of EP1788191A1 publication Critical patent/EP1788191A1/fr
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Publication of EP1788191B1 publication Critical patent/EP1788191B1/fr
Ceased 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/14—Casings modified therefor
    • 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
    • F01D3/00—Machines or engines with axial-thrust balancing effected by working-fluid
    • F01D3/04—Machines or engines with axial-thrust balancing effected by working-fluid axial thrust being compensated by thrust-balancing dummy piston or the like
    • 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
    • F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
    • F01D5/084—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades the fluid circulating at the periphery of a multistage rotor, e.g. of drum type
    • 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
    • F01D9/00—Stators
    • F01D9/06—Fluid supply conduits to nozzles or the like
    • F01D9/065—Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids
    • 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
    • F05D2240/00—Components
    • F05D2240/20—Rotors
    • F05D2240/24—Rotors for turbines
    • F05D2240/242—Rotors for turbines of reaction type
    • 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 invention relates to a steam turbine with a high-pressure turbine part and a fluidically connected with this medium-pressure turbine section, which part turbines are arranged on a common turbine shaft.
  • Known steam turbines are divided into constant pressure turbines and overpressure turbines. Both turbine types have a turbine shaft with blades disposed thereon and an inner shell with vanes disposed between the axially spaced blades. The turbine types differ mainly in the design of their vanes and blades.
  • an overpressure turbine is carried out in drum construction.
  • the blades are arranged directly on the circumference.
  • the vanes are either inserted directly into the housing of the steam turbine or into a special vane carrier.
  • a series of vanes and a downstream row of blades form a vane stage.
  • the guide and blade profiles have a similar shape, resulting in a degree of reaction of about 0.5% of the stage.
  • the percentage distribution of the enthalpy drop across the blades ⁇ h " ⁇ under reaction degree based on the enthalpy of the level ⁇ h ges at a stage of a thermal turbomachine understood ⁇ ⁇ H ⁇ ⁇ H ges ,
  • the degree of reaction ⁇ applies to the static enthalpy differences, ie the velocity components are neglected or assumed to be the same size.
  • a turbine shaft is mounted in an outer housing with a high pressure turbine and a medium pressure turbine disposed along the turbine shaft.
  • the high-pressure turbine is designed in the manner of a constant-pressure turbine and the medium-pressure turbine in the manner of an overpressure turbine.
  • a thrust balance piston is provided, which steam outlet side arranged to the high-pressure turbine and is connected via a pressure line to a steam outlet of the medium-pressure turbine.
  • the invention has for its object to provide a combined high-pressure / medium-pressure steam turbine, in which the thermal load of the turbine shaft is reduced in the medium-pressure turbine by a small design effort. Furthermore, the invention has for its object to provide a method for cooling such a steam turbine.
  • the first object is achieved by a steam turbine with a high-pressure turbine part and a fluidically connected with this medium-pressure turbine, which part turbines are arranged on a common turbine shaft, wherein a cooling line is provided via the exhaust steam from the high-pressure turbine section for cooling purposes the medium-pressure turbine section can be fed.
  • the main advantage of this design is the fact that the relatively cool exhaust steam from the high-pressure turbine section is used by low design effort for cooling the elements of the medium-pressure turbine section.
  • the live steam which is fed at a pressure of about, for example, 125 bar in the high-pressure turbine section, cools during its expansion and leaves at a pressure of, for example, 33 bar and a temperature of for example 350 ° C, the high-pressure turbine section.
  • the evaporation temperature is lower than the temperature of the steam from a reheater (hot-reheat steam: HZU steam) by about 200 ° C, which is fed as HZÜ steam in the medium-pressure turbine section.
  • a lower mechanical utilization of the shaft in the medium-pressure turbine section allows higher steam temperatures and thus higher cycle efficiencies. This is achieved by selectively cooling the elements of the medium-pressure turbine section, which are directly exposed to HZÜ steam, with the cooler exhaust steam from the high-pressure turbine section.
  • the first blade row is made shorter than would be optimal in terms of flow, in order to reduce the stresses from centrifugal forces. Due to the present modification of the steam turbine, which ensures effective cooling of the turbine shaft, the lossy reduction of the blade height is no longer necessary. Thus, an optimal dimensioning of the guide and moving blades of the first stage can be realized.
  • At least one of the sub-turbines is designed as an overpressure turbine in drum construction.
  • Both sub-turbines run in barrel construction.
  • An overpressure turbine characterized by a drum design, is particularly suitable for use in steam power plants and combined cycle (combined cycle) power plants.
  • the cooling line opens in the region of the turbine shaft close to a first blade stage of the medium-pressure turbine section.
  • the first stage of the turbine blading is subjected to the strongest thermal and mechanical loads, therefore targeted cooling of the first blade stage results in a reduced utilization of the turbine shaft.
  • the cooling line opens into a relief groove, which is mounted on the turbine shaft in front of the first blade stage of the medium-pressure turbine section.
  • the turbine shaft is cooled particularly effectively by the outlet of the cooling line in the region of an inflow region of the HZÜ steam is mounted in the immediate vicinity of the turbine shaft so that the cooler exhaust steam can cool the material of the turbine shaft before the exhaust steam with the HZÜ steam mixed.
  • the cooling line is at least indirectly connected to a Abdampfraum the high-pressure turbine section.
  • This Abdampfraum is located in the housing of the high-pressure turbine section.
  • a further improvement of the medium-pressure turbine part is preferably achieved in that a flow connection is provided, which connects the relief groove with a region in which a second blade stage is held positively, so that the turbine shaft active in the second stage with Abdampf from the High-pressure turbine section is cooled.
  • this flow connection is a bore through the turbine shaft.
  • the cooling line is a thrust equalization line, which fluidly connects the high-pressure turbine section with the medium-pressure turbine section to compensate for the axial thrust.
  • the existing in most combined steam turbines according to the preamble already existing thrust compensation line reduces the design effort to a minimum by the thrust balance line or a branch of the thrust balance line is guided only to the relief groove on the turbine shaft to the area before the first stage of the medium-pressure turbine part targeted To cool Abdampf from the Abdampfraum.
  • the first blade stage of the medium-pressure turbine part is designed in the manner of a low-reaction stage with a designed as a fixed guide ring stator.
  • the high-pressure turbine section and the medium-pressure turbine section are arranged in a common outer housing.
  • the two sub-turbines therefore form a combined unit.
  • the second object is achieved according to the invention by a method for cooling a steam turbine with a high-pressure turbine section and a fluidically connected with this medium-pressure turbine section, which are arranged on a common turbine turbine turbine, where exhaust steam from the high pressure turbine section for cooling purposes in the medium pressure Partial turbine is supplied via a cooling line.
  • FIG. 1 shows a steam turbine 2, which has an outer housing 4. Through the outer housing 4 directed along a turbine axis turbine shaft 6 is guided. The turbine shaft 6 has at one end a shaft coupling 8 for coupling to a low-pressure turbine part, not shown, or to a generator, not shown. Within the outer housing 4, an inner housing 10 is arranged around the turbine shaft 6.
  • a high-pressure turbine part 12 and a medium-pressure turbine part 14 are arranged on the turbine shaft 6, wherein both are formed in a drum construction. These comprise guide vanes 16 connected to the inner housing 10 and rotor blades 18 connected to the turbine shaft 6 which extend around the circumference of the turbine shaft 6 in the form of alternating vane rings and blade rings. This is indicated in the figure by the first blade stage 20 of the medium-pressure turbine part 14. Since both the high-pressure turbine section 12 and the medium-pressure turbine section 14 is an overpressure turbine, their guide vanes 16 and blades 18 have a similar structure, so that the pressure is dissipated equally across the vanes 16 and blades 18 of a stage 20. As a result, for example, a degree of reaction in the range 0.3 to 0.5 is set.
  • first stage 20 of the medium-pressure turbine section 14 in which the guide vanes 16 are inclined relative to the rotor blades 18 (diagonal stage) and shorter.
  • This is a so-called low-reaction stage, which has a degree of reaction between 0.1 and 0.25.
  • Axially between the high-pressure turbine section 12 and the medium-pressure turbine section 14 is formed a large intermediate bottom 22 of the turbine shaft 6 serving for thrust compensation, which is a shaft seal.
  • Front side on both sides of the intermediate bottom 22, the turbine shaft 6 each have a relief groove 24, 26.
  • the relief groove 24 is located in an inflow region 28a of the high-pressure turbine section 12, and the relief groove 26 is located in an inflow region 28b of the medium-pressure turbine section 14.
  • Abdampfraum 30 From Abdampfraum 30 an exhaust steam A via a discharge line 32 out of the steam turbine 2 is led out.
  • the exhaust steam A is reheated in an unrepresented reheater, it is supplied as HZÜ steam G at a temperature of, for example, 560 ° C and a pressure of 30 bar of the medium-pressure turbine section 14 in the inflow 28b. After relaxing and cooling it passes at a pressure of about 3 to 6 bar in a discharge region 34 of the medium-pressure turbine section 14 and is led out of the steam turbine 2.
  • the drum construction with positive pressure blading of both sub-turbines 12, 14 leads to an axial thrust in the direction of the steam outlet of each sub-turbine 12, 14.
  • a piston 36 is provided to accommodate the axial thrust of the medium-pressure turbine section 14, so that the high-pressure turbine part 12 is arranged axially between the piston 36 and the large intermediate bottom 22.
  • a smaller intermediate bottom 37 is arranged, which is also formed in the manner of a shaft seal.
  • the piston 36 is fluidly connected via a thrust balance line 38 with the medium-pressure turbine section 14.
  • the thrust balance line 38 is formed such that at least one branch opens into the relief groove 26.
  • the thrust balance line 38 opens completely into the relief groove 26 below the guide ring.
  • the thrust balance line 38 is fluidically connected to the Abdampfraum 30, so that the exhaust steam A is fed at a temperature of about 350 ° C via the thrust balance line 38 directly into the relief groove 26.
  • the thrust balance line 38 also serves as a cooling line.
  • the two openings of the thrust balance line 38 are positioned in such a way and shaft seals are, if necessary, designed such that a pressure gradient in the direction of opening into the relief groove 26 opening of the thrust equalization line 38 is. This ensures a continuous influx of cold exhaust steam A into the relief groove 26.
  • FIG. 2 shows an enlargement of the inflow region 28b of the medium-pressure turbine section 14 with the first blade stage 20.
  • a 26 holes 40 are provided in the axial direction in the relief groove. These holes 40 connect the relief groove 26 fluidly with a region in which a second blade ring (not shown here) is positively secured to the turbine shaft 6.
  • the bores 40 in this case have outlet openings 42 in particular to a blade chamber 44, which is traversed by the HZÜ vapor G.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP20050025245 2005-11-18 2005-11-18 Turbine à vapeur et procédé pour le refroidissement d'une turbine à vapeur Ceased EP1788191B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP20050025245 EP1788191B1 (fr) 2005-11-18 2005-11-18 Turbine à vapeur et procédé pour le refroidissement d'une turbine à vapeur

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP20050025245 EP1788191B1 (fr) 2005-11-18 2005-11-18 Turbine à vapeur et procédé pour le refroidissement d'une turbine à vapeur

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EP1788191A1 true EP1788191A1 (fr) 2007-05-23
EP1788191B1 EP1788191B1 (fr) 2014-04-02

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Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH701914A1 (de) * 2009-09-30 2011-03-31 Alstom Technology Ltd Dampfturbine mit Entlastungsnut am Rotor im Bereich des Schubausgleichskolbens.
EP2412937A1 (fr) * 2010-07-30 2012-02-01 Siemens Aktiengesellschaft Turbine à vapeur et procédé de refroidissement de celle-ci
EP3130748A1 (fr) * 2015-08-14 2017-02-15 Siemens Aktiengesellschaft Refroidissement de rotor pour une turbine a vapeur

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3614255A (en) * 1969-11-13 1971-10-19 Gen Electric Thrust balancing arrangement for steam turbine
SU1216373A1 (ru) * 1984-02-16 1986-03-07 Предприятие П/Я А-3513 Цилиндр турбомашины
US5263997A (en) * 1992-03-27 1993-11-23 Westinghouse Electric Corp. Flange bolt load spreading plate
JPH09125909A (ja) * 1995-10-30 1997-05-13 Mitsubishi Heavy Ind Ltd 複合サイクル用蒸気タービン
DE19700899A1 (de) 1997-01-14 1998-07-23 Siemens Ag Dampfturbine
JPH11200801A (ja) * 1998-01-14 1999-07-27 Mitsubishi Heavy Ind Ltd 蒸気タービンのロータ冷却装置
EP1154123A1 (fr) * 2000-05-10 2001-11-14 Siemens Aktiengesellschaft Procédé de refroidissement pour l'arbre d'une turbine à vapeur à haute pression
US20040247433A1 (en) * 2003-02-05 2004-12-09 Detlef Haje Steam turbine rotor, steam turbine and method for actively cooling a steam turbine rotor and use of active cooling
GB2409002A (en) * 2003-12-08 2005-06-15 Siemens Power Generation Ltd Thrust balance piston fitted between high and low pressure paths in a turbine.

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3614255A (en) * 1969-11-13 1971-10-19 Gen Electric Thrust balancing arrangement for steam turbine
SU1216373A1 (ru) * 1984-02-16 1986-03-07 Предприятие П/Я А-3513 Цилиндр турбомашины
US5263997A (en) * 1992-03-27 1993-11-23 Westinghouse Electric Corp. Flange bolt load spreading plate
JPH09125909A (ja) * 1995-10-30 1997-05-13 Mitsubishi Heavy Ind Ltd 複合サイクル用蒸気タービン
DE19700899A1 (de) 1997-01-14 1998-07-23 Siemens Ag Dampfturbine
JPH11200801A (ja) * 1998-01-14 1999-07-27 Mitsubishi Heavy Ind Ltd 蒸気タービンのロータ冷却装置
EP1154123A1 (fr) * 2000-05-10 2001-11-14 Siemens Aktiengesellschaft Procédé de refroidissement pour l'arbre d'une turbine à vapeur à haute pression
US20040247433A1 (en) * 2003-02-05 2004-12-09 Detlef Haje Steam turbine rotor, steam turbine and method for actively cooling a steam turbine rotor and use of active cooling
GB2409002A (en) * 2003-12-08 2005-06-15 Siemens Power Generation Ltd Thrust balance piston fitted between high and low pressure paths in a turbine.

Non-Patent Citations (3)

* Cited by examiner, † Cited by third party
Title
PATENT ABSTRACTS OF JAPAN vol. 1997, no. 09 30 September 1997 (1997-09-30) *
PATENT ABSTRACTS OF JAPAN vol. 1999, no. 12 29 October 1999 (1999-10-29) *
PATERSON A N ET AL: "STEAM TURBINES FOR ADVANCED STEAM CONDITIONS", TECHNICAL REVIEW GEC ALSTHOM, GEC ALSTHOM, PARIS, FR, no. 17, 1 June 1995 (1995-06-01), pages 1 - 16, XP000526077, ISSN: 1148-2893 *

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH701914A1 (de) * 2009-09-30 2011-03-31 Alstom Technology Ltd Dampfturbine mit Entlastungsnut am Rotor im Bereich des Schubausgleichskolbens.
US8684663B2 (en) 2009-09-30 2014-04-01 Alstom Technology Ltd. Steam turbine with relief groove on the rotor
EP2412937A1 (fr) * 2010-07-30 2012-02-01 Siemens Aktiengesellschaft Turbine à vapeur et procédé de refroidissement de celle-ci
WO2012013531A1 (fr) * 2010-07-30 2012-02-02 Siemens Aktiengesellschaft Turbine à vapeur et procédé pour refroidir une turbine à vapeur
EP3130748A1 (fr) * 2015-08-14 2017-02-15 Siemens Aktiengesellschaft Refroidissement de rotor pour une turbine a vapeur
WO2017029008A1 (fr) * 2015-08-14 2017-02-23 Siemens Aktiengesellschaft Refroidissement de rotor pour turbine à vapeur
CN107923246A (zh) * 2015-08-14 2018-04-17 西门子公司 用于蒸汽轮机的转子冷却

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Publication number Publication date
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