EP0953100B1 - Dampfturbine - Google Patents

Dampfturbine Download PDF

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Publication number
EP0953100B1
EP0953100B1 EP98904018A EP98904018A EP0953100B1 EP 0953100 B1 EP0953100 B1 EP 0953100B1 EP 98904018 A EP98904018 A EP 98904018A EP 98904018 A EP98904018 A EP 98904018A EP 0953100 B1 EP0953100 B1 EP 0953100B1
Authority
EP
European Patent Office
Prior art keywords
turbine
steam
reaction
pressure
degree
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
EP98904018A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP0953100A1 (de
Inventor
Heinrich Oeynhausen
Wilfried Ulm
Mikhail Simkine
Jan-Erik MÜHLE
Ingo Stephan
Volker Simon
Ralf Bell
Ulrich Capelle
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.)
Siemens AG
Original Assignee
Siemens AG
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Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Publication of EP0953100A1 publication Critical patent/EP0953100A1/de
Application granted granted Critical
Publication of EP0953100B1 publication Critical patent/EP0953100B1/de
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
    • 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
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/142—Shape, i.e. outer, aerodynamic form of the blades of successive rotor or stator blade-rows
    • 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

Definitions

  • the invention relates to a steam turbine with a a turbine axis directed turbine shaft, wherein along the turbine shaft comprising a plurality of turbine stages each a vane structure and one of these axially downstream blade assembly are provided.
  • Known steam turbines are used in action turbines (too Constant pressure turbines) and reaction turbines (also Called overpressure turbines). They have a turbine shaft with blades arranged on it and an inner housing with blades arranged between axially spaced barrels Guide vanes on.
  • the isentropic reaction degree r for a thermal Fluid machine the percentage distribution of the isentropic Enthalpy gradient in the blades to the entire isentropic Enthalpy gradient over a step consisting of vane ring and designated blade ring.
  • the classic overpressure level as well as the Equal pressure level applied. The latter usually with a slightly different degree of reaction r.
  • chamber turbine and drum turbine are also used used.
  • a chamber turbine has a housing which by spaced axially spaced shelves is divided into several chambers. In each of these Chambers runs a disc-shaped impeller on its outer circumference the blades are attached while the guide blades are inserted in the intermediate floors.
  • An advantage the chamber design is that the shelves on their The inner edge is quite effective using labyrinth seals the turbine shaft can be sealed. Because the gasket knife is small, the gap cross sections and thus the gap leakage currents are small.
  • Turbines only with small degrees of reaction, i.e. large ones Gradient slope and thus low number of stages used. The Pressure difference on both sides of an impeller disc low with a low degree of reaction, in the limit case even zero. An axial thrust exerted on the rotor remains low and can be taken up by a thrust bearing.
  • the blades are immediate in a drum turbine arranged on the circumference of a drum-shaped turbine shaft.
  • the Guide vanes are either directly in the housing of the steam turbine or used in a special guide vane carrier.
  • DE-AS 20 54 465 is a steam turbine in drum design described.
  • a pot-shaped outer housing one is the Run blades carrying the turbine shaft and a turbine shaft surrounding inner housing arranged.
  • the inner case carries the guide vanes. Via appropriate storage and centering points is the inner housing with the outer housing Recording an axial thrust connected.
  • DE-PS 312 856 is a high-pressure steam turbine Degree of reaction described, with several step groups in are arranged in a housing. In the different turbine stages different degrees of reaction are achieved a degree of reaction of well over 0.5 at the beginning and of have significantly less than 0.5 at the end of the group. from one another axially spaced steps each have a different Degree of reaction to. There are several turbine stages combined into subgroups, with several subgroups one Form overpressure blade group. In a first overpressure blade group the degree of reaction decreases in each subgroup towards the steam outlet, the average degree of reaction of the subgroups towards the steam outlet, however. In the second, pressure group associated with the steam outlet the degree of reaction towards the steam outlet in each subgroup. The average degree of reaction has a local maximum.
  • DE-PS 880 307 an overpressure steam turbine, which in Drum construction is specified.
  • the steam turbine is designed so that the degree of reaction down to the last stage the previous stages to the evaporation area continuously increases and is well above 0.5. Only in In the last stage, the degree of reaction drops to a value of less than 0.5.
  • DE-A-3 006 286 there is a positive pressure steam turbine described with a constant pressure control stage.
  • the object of the invention is to provide a steam turbine with a good To indicate efficiency.
  • the object is achieved by a steam turbine with a turbine shaft directed along a turbine axis, wherein a plurality of Turbine stages each include a vane structure and one of these axially downstream rotor blade arrangement is provided is, with at least two turbine stages each different average degree of reaction achievable and the degree of reaction is over half the Turbine levels are less than 0.5.
  • the degree of reaction at the steam inlet is between 0.2 and 0.4, especially between 0.25 and 0.35, as well as at the steam outlet between 0.4 and 0.6, in particular between 0.45 and 0.55.
  • the average degree of reaction (average step reaction) the ratio of those in the blade assembly of the Turbine stage implemented enthalpy gradient to the entire enthalpy gradient implemented in the turbine stage.
  • a variable design of the degree of reaction depends on Areas of application of the steam turbine achieve a high degree of efficiency.
  • the degree of reaction varies in a steam turbine, through which superheated steam flows into a steam inlet and flows out of a steam outlet after axial flow, between steam inlet and steam outlet.
  • the degree of reaction varies preferably from turbine stage to turbine stage, so that taking into account steam pressure, steam temperature, Steam mass flow for each turbine stage with regard to one particularly high efficiency and a favorable average degree of reaction can already be determined when designing the steam turbine is.
  • the average degree of reaction varies with a steam turbine, in particular a partial turbine in drum design, at least in some areas between 5% and 70%, in particular between 10% and 50%, preferably below 45%.
  • He can depending on the area of application from turbine stage to turbine stage rise, fall or first a local extremum (Maximum and / or minimum).
  • a local maximum low i.e. it deviates by 0.1 the value of the degree of reaction at the steam inlet or outlet from.
  • the course of the degree of reaction is preferably monotonic falling or increasing monotonously.
  • the degree of reaction preferably varies (Difference between two turbine stages) by 0.1, in particular by more than 0.2.
  • the middle Degree of reaction preferably between 5% and 35%, in particular less than 20%.
  • the turbine stages are, particularly in the case of a medium-pressure partial turbine summarized in step groups, at least the degree of reaction of a turbine stage of a first stage group is different from the degree of reaction of a turbine stage a second tier group. It is also possible in the high-pressure sub-turbine to provide step groups.
  • High-pressure sub-turbine and medium-pressure sub-turbine can in a separate outer housing or in a common one Outer housing (compact turbine) can be arranged. It is also possible to use a medium-pressure partial turbine in drum design and an upstream high-pressure turbine section in Chamber design.
  • the high pressure part turbine in Drum design can be arranged in a pot-shaped outer housing his.
  • the outer casing of the high-pressure turbine section can also be carried out in two axially divided halves.
  • the degree of reaction between successive in the direction of flow Turbine stages can thus be designed in various ways.
  • the Degree of reaction can vary from turbine stage to turbine stage take different values, especially in the direction of flow decrease or increase continuously.
  • the steam turbine steam pressure, steam temperature, mass flow as well as electrical and thermal power
  • a steam turbine with a particularly good one Efficiency can be produced in the required area of application.
  • both a high pressure turbine and also a medium-pressure partial turbine in drum design can be and one turbine stage or several turbine stages, if not all turbine stages, with one average degree of reaction below 50%, in particular below 45% can be executed.
  • Figure 1 shows a steam turbine 1 with a single outer housing 4. Through the outer casing is one along a turbine axis 15 directed turbine shaft 6 out. This turbine shaft 6 is on the bushings not shown with respective shaft seals 9 with respect to the outer housing 4 sealed.
  • a high-pressure turbine section 2 arranged in chamber design. This indicates a high-pressure blading with the turbine shaft 6 connected blade assemblies 11 and with a high pressure inner housing 14 connected shown schematically Guide vane structures 12.
  • the turbine shaft 6 has one End a shaft coupling 10 for coupling to one not shown generator or a low-pressure turbine part, not shown on.
  • Axial between the high pressure blading and the medium pressure blading is an area 13 (Intermediate floor) of the turbine shaft 6, which opposite the inner housing 14 by a corresponding shaft seal 9 is sealed.
  • the turbine shaft 6 Towards the medium pressure turbine section 3 the turbine shaft 6 has a recess in the intermediate floor 13 13a, through the end faces on the intermediate floor 13 are formed.
  • the intermediate floor 13 is fluidically with an inflow region 7b of the medium-pressure turbine section 3 connected to a steam inlet 7a of the high pressure turbine section 2.
  • the steam which is now partially relaxed, reaches a Reheating, not shown, and the steam turbine 1 via the steam inlet 7b of the medium-pressure turbine section 3 fed again.
  • Each by a guide vane structure 12 and a Blade arrangement 11 downstream in the direction of flow Formed turbine stages 17a, 17b, 17c are in three stage groups 18a, 18b, 18c divided.
  • the degree of reaction can be also decrease according to the intended application of the steam turbine or alternately rise and fall. It is also possible that the degree of reaction of turbine stages 17a, 17b, 17c of a respective step group 18a, 18b, 18c varies, in particular in the direction of the steam outlet 8b from the turbine stage varies at turbine level.
  • a thrust compensation piston 5 is provided, which via a pressure line 16 connected to the steam outlet 8b of the medium-pressure turbine section 3 is.
  • This thrust compensation piston 5 is on the steam outlet side arranged to the high-pressure turbine section 2, so that this axially between the thrust compensation piston 5 and the intermediate floor 13, i.e. the medium-pressure turbine 3 is arranged.
  • the steam turbine 1 can be analogous to the embodiment according to FIG. 1 a low-pressure turbine part can be connected.
  • FIG. 2 shows a steam turbine 1 with a high-pressure partial turbine 2 with an outer housing 4a and one of them axially spaced medium-pressure turbine section 3 with an outer casing 4b.
  • the medium-pressure turbine section 3 is designed with two passages.
  • a turbine shaft passed through the outer casing 4a 6a of the high pressure turbine section 2 is via a shaft coupling 10 with a through the outer casing 4b of the medium-pressure turbine 3 guided turbine shaft 6b coupled.
  • On the turbine shaft 6b is a further shaft coupling 10 for coupling to a generator or not shown Low-pressure turbine part arranged.
  • the high pressure turbine is in drum design and the medium pressure turbine executed in chamber construction.
  • Axial between steam inlet 7a and housing 4a is a thrust compensating piston 5 trained intermediate floor arranged.
  • the guide vane structures are in the high-pressure sub-turbine 2 12 in an axially continuous inner housing 14 without Subdivided into groups of levels.
  • the degree of reaction a turbine stage 17a is greater than the degree of reaction one Downstream turbine stage 17b.
  • a steam flow is axial from the steam inlet 7a directed towards the steam outlet 8a.
  • FIG. 3 shows four curves 20a, 20b, 20c and 20d the course of the degree of reaction r over a plurality (here 14) downstream turbine stages as an example shown.
  • Turbine stage number 1 is one Steam inlet area 7a, 7b assigned and the turbine stage No. 14 a steam outlet 8a, 8b.
  • the course of the degree of reaction r according to curve 20a begins at turbine stage no Value 0.1 and increases for those downstream in the flow direction Turbine levels continuously down to approximately 0.55 at.
  • the degree of reaction r has at the turbine stage No. 1 a value of 0.5, falls to turbine level No. 9 continuously decreases, has a minimum value of about 0.25, rises again continuously to turbine stage 12 to a value of around 0.3 and falls to turbine stage no.14 to a value of 0.275.
  • the fourth curve 20d lies in one monotonically increasing band range of the average degree of reaction.
  • the band area has a bandwidth between steam inlet 7a, 7b and steam outlet 8a, 8b of the order of 0.2.
  • the band area at turbine stage no. 1 is between about 0.2 and 0.4 and at turbine stage No. 14 between about 0.4 and 0.6.
  • the invention is characterized by a steam turbine, which a degree of reaction for a turbine stage between 5% and has 75%.
  • the average degree of reaction preferably proceeds successive turbine stages in the direction of flow between steam inlet 7a, 7b and steam outlet 8a, 8b in essentially monotonous. Depending on the area of application of the steam turbine it can increase, decrease or alternate.

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)
EP98904018A 1997-01-14 1998-01-09 Dampfturbine Expired - Lifetime EP0953100B1 (de)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE19701020 1997-01-14
DE19701020A DE19701020A1 (de) 1997-01-14 1997-01-14 Dampfturbine
PCT/DE1998/000063 WO1998031923A1 (de) 1997-01-14 1998-01-09 Dampfturbine

Publications (2)

Publication Number Publication Date
EP0953100A1 EP0953100A1 (de) 1999-11-03
EP0953100B1 true EP0953100B1 (de) 2002-04-10

Family

ID=7817350

Family Applications (1)

Application Number Title Priority Date Filing Date
EP98904018A Expired - Lifetime EP0953100B1 (de) 1997-01-14 1998-01-09 Dampfturbine

Country Status (7)

Country Link
US (1) US6345952B1 (ru)
EP (1) EP0953100B1 (ru)
JP (1) JP2001510525A (ru)
CN (1) CN1084822C (ru)
DE (2) DE19701020A1 (ru)
RU (1) RU2189449C2 (ru)
WO (1) WO1998031923A1 (ru)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE202010012298U1 (de) 2010-09-07 2010-11-18 Alstom Technology Ltd. Gas.bzw. Dampfturbine
DE102015223212A1 (de) * 2015-11-24 2017-05-24 MTU Aero Engines AG Verfahren, Verdichter und Strömungsmaschine

Families Citing this family (22)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR20020028221A (ko) 1999-08-27 2002-04-16 칼 하인쯔 호르닝어 터빈 및 누출 유체를 방출시키기 위한 방법
EP1154123A1 (de) 2000-05-10 2001-11-14 Siemens Aktiengesellschaft Verfahren zur Kühlung einer Welle in einem Hochdruck-Expansionsabschnitt einer Dampfturbine
ES2267655T3 (es) 2001-11-22 2007-03-16 Siemens Aktiengesellschaft Metodo de fabricacion de turbinas de vapor.
JP2005522629A (ja) 2002-04-11 2005-07-28 エイ． ハーゼ，リチャード 水燃焼技術−水素と酸素を燃焼させる方法、プロセス、システム及び装置
US6783321B2 (en) * 2002-11-06 2004-08-31 General Electric Company Diffusing coupling cover for axially joined turbines
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.
US8047767B2 (en) * 2005-09-28 2011-11-01 General Electric Company High pressure first stage turbine and seal assembly
MD3892G2 (ru) * 2007-10-29 2009-11-30 Виктор ИВАНОВ Паровая турбина барабанного типа
US8221056B2 (en) * 2009-06-11 2012-07-17 General Electric Company Mixing hotter steam with cooler steam for introduction into downstream turbine
DE102011006065B4 (de) 2011-03-24 2014-10-02 Siemens Aktiengesellschaft Dampfturbine mit Dampfsiebanordnungen
DE102011006066B4 (de) 2011-03-24 2016-06-30 Siemens Aktiengesellschaft Wasserseparator und Verfahren zum Abtrennen von Wasser aus einer Nassdampfströmung
DE102011087824A1 (de) 2011-12-06 2013-06-06 Man Diesel & Turbo Se Turbine
US9926843B2 (en) 2012-07-20 2018-03-27 Pratt & Whitney Canada Corp. Compound cycle engine
US10107195B2 (en) * 2012-07-20 2018-10-23 Pratt & Whitney Canada Corp. Compound cycle engine
US9512721B2 (en) 2012-07-20 2016-12-06 Pratt & Whitney Canada Corp. Compound cycle engine
DE102013204002B3 (de) * 2013-03-08 2014-08-28 Siemens Aktiengesellschaft Dampfturbine mit innenliegendem Axialschieber
JP6278329B2 (ja) * 2015-02-23 2018-02-14 三菱重工コンプレッサ株式会社 蒸気タービン
DE102015223210B3 (de) 2015-11-24 2017-04-27 MTU Aero Engines AG Verdichter, Verfahren und Strömungsmaschine
DE102017211295A1 (de) * 2017-07-03 2019-01-03 Siemens Aktiengesellschaft Dampfturbine und Verfahren zum Betreiben derselben
CN108035775A (zh) * 2018-01-08 2018-05-15 翁志远 汽轮机的转子、汽轮机和原动机设备
JP7061557B2 (ja) * 2018-12-07 2022-04-28 三菱重工コンプレッサ株式会社 蒸気タービン
WO2023156049A1 (en) 2022-12-21 2023-08-24 General Electric Technology Gmbh A steam turbine and a use of the steam turbine, a method of manufacturing or servicing of said steam turbine, a small-modular reactor and a power plant including said steam turbine

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FR379478A (fr) * 1906-07-18 1907-11-05 Bbc Brown Boveri & Cie Turbine à vapeur partie à action et partie à réaction
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EP0043602A1 (de) * 1980-07-09 1982-01-13 BBC Aktiengesellschaft Brown, Boveri & Cie. Dampfturbine mit Heizdampfentnahme

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE202010012298U1 (de) 2010-09-07 2010-11-18 Alstom Technology Ltd. Gas.bzw. Dampfturbine
DE102015223212A1 (de) * 2015-11-24 2017-05-24 MTU Aero Engines AG Verfahren, Verdichter und Strömungsmaschine
US10337519B2 (en) 2015-11-24 2019-07-02 MTU Aero Engines AG Method, compressor and turbomachine

Also Published As

Publication number Publication date
RU2189449C2 (ru) 2002-09-20
WO1998031923A1 (de) 1998-07-23
EP0953100A1 (de) 1999-11-03
DE19701020A1 (de) 1998-07-23
CN1084822C (zh) 2002-05-15
CN1242818A (zh) 2000-01-26
JP2001510525A (ja) 2001-07-31
US6345952B1 (en) 2002-02-12
DE59803728D1 (de) 2002-05-16

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