EP0296440A1 - Turbine à vapeur pour des régimes de fonctionnement partiel - Google Patents

Turbine à vapeur pour des régimes de fonctionnement partiel Download PDF

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Publication number
EP0296440A1
EP0296440A1 EP88109355A EP88109355A EP0296440A1 EP 0296440 A1 EP0296440 A1 EP 0296440A1 EP 88109355 A EP88109355 A EP 88109355A EP 88109355 A EP88109355 A EP 88109355A EP 0296440 A1 EP0296440 A1 EP 0296440A1
Authority
EP
European Patent Office
Prior art keywords
swirl
flow
steam turbine
grille
control wheel
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
EP88109355A
Other languages
German (de)
English (en)
Other versions
EP0296440B1 (fr
Inventor
Jürg Dr. Bütikofer
Hans Meyer
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.)
BBC Brown Boveri AG Switzerland
Original Assignee
BBC Brown Boveri AG Switzerland
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 BBC Brown Boveri AG Switzerland filed Critical BBC Brown Boveri AG Switzerland
Publication of EP0296440A1 publication Critical patent/EP0296440A1/fr
Application granted granted Critical
Publication of EP0296440B1 publication Critical patent/EP0296440B1/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
    • F01D1/00—Non-positive-displacement machines or engines, e.g. steam turbines
    • F01D1/02—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines
    • F01D1/16—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines characterised by having both reaction stages and impulse stages
    • 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
    • F01D1/00—Non-positive-displacement machines or engines, e.g. steam turbines
    • F01D1/02—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines
    • F01D1/10—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines having two or more stages subjected to working-fluid flow without essential intermediate pressure change, i.e. with velocity stages

Definitions

  • the invention relates to a steam turbine which is operated in the part-load range with nozzle group control.
  • control wheels with separately opening nozzle groups are used in steam turbine construction, because the efficiency that can be achieved is better than that of other systems over the essential performance range, whereby the control wheel causes work to be extracted from the steam in such a way that the power control itself is optimal works.
  • a compensation room is provided which enables the transition from partial loading to full loading.
  • the invention seeks to remedy this.
  • the invention is based on the object, in steam turbines operated at part load of the type mentioned, to bring about an equalization of the flow at the transition from partial loading in the control stage to the full loading in the remaining stages.
  • the object is primarily achieved by installing a swirl grille behind the control wheel, with the first row of guide vanes from the subsequent blading of the turbine being omitted at the same time.
  • the mode of operation is such that the swirl grille provides the mass flow emerging from the control wheel with a significant swirl before it is released into the overflow channel.
  • the swirl creates an additional pressure gradient in the circumferential direction during partial loading, which creates a tangential compensation flow.
  • Another important advantage of the invention is that the solution can be used equally well, even if there is no difference in diameter between the control wheel and subsequent blading: The space requirement is not greater than in existing control wheel machines, which makes the solution ideal for retrofitting existing systems is suitable.
  • the conventional, first guide vane row is adapted to the flow coming from the swirl grille in such a way that there is less deflection in this guide row.
  • the invention is equally applicable to turbines of the reaction as of the action construction, which is why the exemplary embodiments are to be understood for one or the other type.
  • the diameter of the control wheel 2 is larger than the diameter of the hub 1 and the first row of rotor blades 7.
  • a disk 5 is provided after the control wheel 2, in which a swirl grille 4, which enables the controlled swirl outflow, is installed.
  • the disk 5 is fixed in the stator 10 and extends in its radial plane up to the outer diameter of the hub 1. Seals 6 are provided there, which minimize leakage flow between the control wheel 2 and the disk 5.
  • the swirl grille 4 provides the partial flows emerging from the control wheel 2 with a clear swirl and then releases them into the overflow channel 9.
  • FIG. 2 differs from FIG. 1 only in the design of the overflow duct 9. While in FIG. 1 the overflow duct 9 describes a direct line to the blade rows, the overflow duct according to FIG. 2 has an additional swirl chamber 11, which follows immediately the swirl grid 4 extends into the stator 10 in a bay shape. This swirl chamber 11 is an additional compensation chamber in which the flow is deflected in the direction of the blades 7.
  • FIG. 3 has an additional measure compared to FIG. 2, which in turn pursues the purpose mentioned to apply an optimized flow to the rotor blades 7.
  • a radial guide vane 12 is provided, which enables any swirl correction of the flow. This guide vane 12 is mounted between the stator 10 and disk 5.
  • FIG. 4 shows a further variant for optimizing the swirl effect from the exit of the swirl grid 4.
  • flow guides 13 and 14 which also channel the flow in the overflow channel 9 in terms of space.
  • a first guide 13 forces the flow from the swirl grille 4 to immediately flow through the overflow channel 9.
  • Another guide 14 also runs from the swirl grille 4 in the flow direction parallel to the wall of the transfer channel 9.
  • the flow guide 14 is terminated at the end in the sense of a transition aid for changing the direction of the flow.
  • a swirl correction grid 15 can be provided directly in front of the first row of blades 7.
  • the solution shown in FIG. 5 corresponds to that from FIG. 1 with the difference that two or more partially loaded stages 16 now act in front of the swirl grille 4.
  • a partially loaded guide vane 17 is provided between the partially loaded impellers 16.
  • FIG. 7 shows another type of construction in which the action wheels 20, 21, 22 of the turbine used have no diameter difference compared to the upstream control stage 2, 3.
  • the space 23 is dimensioned such that the swirl flow generated by the swirl grille 4 is not inadmissibly reduced until the action range 20, 21, 22 is fully loaded.
  • FIG. 8 shows the disk 5 and the swirl grid 4 in an axial view.
  • the actively acting swirl grille 4 is reduced to an impingement arc zone 24, with which this acts in accordance with the nozzle grille of the control stage.
  • the rest of the circumference is smooth and serves as additional ventilation protection.
  • the angular dimension of the impingement arch 24 results from the impingement arch of the nozzle grille 4. This embodiment is intended for small mass flows in which the entire circumference of the disk 5 is not required.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Control Of Turbines (AREA)
EP88109355A 1987-06-26 1988-06-13 Turbine à vapeur pour des régimes de fonctionnement partiel Expired - Lifetime EP0296440B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH2426/87A CH672817A5 (fr) 1987-06-26 1987-06-26
CH2426/87 1987-06-26

Publications (2)

Publication Number Publication Date
EP0296440A1 true EP0296440A1 (fr) 1988-12-28
EP0296440B1 EP0296440B1 (fr) 1993-01-27

Family

ID=4233533

Family Applications (1)

Application Number Title Priority Date Filing Date
EP88109355A Expired - Lifetime EP0296440B1 (fr) 1987-06-26 1988-06-13 Turbine à vapeur pour des régimes de fonctionnement partiel

Country Status (4)

Country Link
US (1) US4881872A (fr)
EP (1) EP0296440B1 (fr)
CH (1) CH672817A5 (fr)
DE (1) DE3877839D1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0982474A1 (fr) * 1998-08-28 2000-03-01 Asea Brown Boveri AG Turbine à vapeur

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5116200A (en) * 1990-06-28 1992-05-26 General Electric Company Apparatus and methods for minimizing vibrational stresses in axial flow turbines
US5236349A (en) * 1990-10-23 1993-08-17 Gracio Fabris Two-phase reaction turbine
DE59808650D1 (de) 1998-12-16 2003-07-10 Alstom Switzerland Ltd Modulare Dampfturbine mit Standardbeschaufelung
US8313292B2 (en) * 2009-09-22 2012-11-20 Siemens Energy, Inc. System and method for accommodating changing resource conditions for a steam turbine

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US797064A (en) * 1905-01-12 1905-08-15 Tore Gustaf Emanuel Lindmark Elastic-fluid turbine.
DE520226C (de) * 1931-03-16 Siemens Schuckertwerke Akt Ges Vorrichtung zum Ausgleich des Axialschubes einer UEberdruckturbine
DE694316C (de) * 1938-06-21 1940-07-29 Aeg Axial beaufschlagte Dampfturbine mit teilbeaufschlagtem Hochdruckrad grossen Durchmessers
DE713016C (de) * 1939-07-28 1941-10-30 Aeg Axial beaufschlagte Dampfturbine mit teilbeaufschlagtem Hochdruckrad grossen Durchmessers
DE3006286A1 (de) * 1980-02-01 1981-08-06 BBC AG Brown, Boveri & Cie., Baden, Aargau Ueberdruckdampfturbine mit einer gleichdruckregelstufe

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1542453A (en) * 1921-08-04 1925-06-16 Westinghouse Electric & Mfg Co Marine turbine
DE599042C (de) * 1932-08-24 1934-06-25 Siemens Schuckertwerke Akt Ges Einrichtung zur Verhuetung einer Wasserausscheidung an den Leitschaufeln von Dampfturbinen
US2187778A (en) * 1936-07-22 1940-01-23 Gardner Mfg Company Humidifier
NL69939C (fr) * 1942-07-30
DE2015056A1 (de) * 1969-03-31 1970-10-08 Rotax Ltd., London Turbine
SE406624B (sv) * 1977-07-12 1979-02-19 Stal Laval Turbin Ab Turbomaskin

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE520226C (de) * 1931-03-16 Siemens Schuckertwerke Akt Ges Vorrichtung zum Ausgleich des Axialschubes einer UEberdruckturbine
US797064A (en) * 1905-01-12 1905-08-15 Tore Gustaf Emanuel Lindmark Elastic-fluid turbine.
DE694316C (de) * 1938-06-21 1940-07-29 Aeg Axial beaufschlagte Dampfturbine mit teilbeaufschlagtem Hochdruckrad grossen Durchmessers
DE713016C (de) * 1939-07-28 1941-10-30 Aeg Axial beaufschlagte Dampfturbine mit teilbeaufschlagtem Hochdruckrad grossen Durchmessers
DE3006286A1 (de) * 1980-02-01 1981-08-06 BBC AG Brown, Boveri & Cie., Baden, Aargau Ueberdruckdampfturbine mit einer gleichdruckregelstufe

Non-Patent Citations (2)

* Cited by examiner, † Cited by third party
Title
A. STODOLA: "Dampf- und Gasturbinen", 5. Auflage, 1922, Seiten 496-506, Verlag von Julius Springer, Berlin, DE *
W. TRAUPEL: "Thermische Turbomaschinen", 3. Auflage, 1977, Seiten 145-160, Springer Verlag, Berlin, DE *

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0982474A1 (fr) * 1998-08-28 2000-03-01 Asea Brown Boveri AG Turbine à vapeur

Also Published As

Publication number Publication date
EP0296440B1 (fr) 1993-01-27
US4881872A (en) 1989-11-21
CH672817A5 (fr) 1989-12-29
DE3877839D1 (de) 1993-03-11

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