EP1335110A1 - Turbomachine avec des aubages à haute pression et basse pression - Google Patents

Turbomachine avec des aubages à haute pression et basse pression Download PDF

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Publication number
EP1335110A1
EP1335110A1 EP02002719A EP02002719A EP1335110A1 EP 1335110 A1 EP1335110 A1 EP 1335110A1 EP 02002719 A EP02002719 A EP 02002719A EP 02002719 A EP02002719 A EP 02002719A EP 1335110 A1 EP1335110 A1 EP 1335110A1
Authority
EP
European Patent Office
Prior art keywords
blade
flow
rotor
region
area
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
EP02002719A
Other languages
German (de)
English (en)
Other versions
EP1335110B1 (fr
Inventor
Gerhard Klaus
Ingo Stephan
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
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 Siemens AG filed Critical Siemens AG
Priority to EP02002719A priority Critical patent/EP1335110B1/fr
Priority to DE50209157T priority patent/DE50209157D1/de
Priority to ES02002719T priority patent/ES2278821T3/es
Priority to JP2003021454A priority patent/JP2003239704A/ja
Priority to US10/359,229 priority patent/US6851927B2/en
Priority to CNB031025021A priority patent/CN1313704C/zh
Publication of EP1335110A1 publication Critical patent/EP1335110A1/fr
Application granted granted Critical
Publication of EP1335110B1 publication Critical patent/EP1335110B1/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
    • F01D1/04—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 traversed by the working-fluid substantially axially
    • 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
    • F01D1/023—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 the working-fluid being divided into several separate flows ; several separate fluid flows being united in a single flow; the machine or engine having provision for two or more different possible fluid flow paths

Definitions

  • the invention relates to a fluid flow machine, the one Housing with a rotating rotor with three blade areas has that are fluidically connected. she further relates to a method for operating the aforementioned Turbomachine as a steam turbine.
  • turbo machines which have a high pressure steam and Low pressure steam range, can be housed or be built in two housings.
  • 1997P03012 DE there are Turbomachines, in particular steam turbines shown.
  • the two-housing version is not part of the technical field of the present invention and therefore will not continue shown.
  • the single-case version consists of one Rotor with two single-flow blade areas to the respective Point housing ends.
  • a bucket area is called High pressure steam scoop area executed and another Bucket area as low pressure steam area.
  • inflowing Live steam first flows through the axial direction Blade area of the high pressure steam blade area. From there the now partially expanded steam passes through a pipe to the medium pressure steam blade area.
  • a disadvantage of these known embodiments with High pressure expansion area is the concern of superheated steam Inside a turbine end.
  • the energetic Steam between the sealing shells is partly in Blading areas with lower temperature for thermodynamic process optimization. This leads the sealing shell steam introduction into the Blading areas on the one around the housing unbalanced housing heating, the thermal stresses and results in deformation, i.e. a warp of the Housing that may rub against Can lead to blades on the housing.
  • the present invention is therefore based on the object based on a single-case fluid machine design that no return of sealing shell steam with regard to thermodynamic process optimization necessary is.
  • Another object of the present invention is to provide a Specify procedures for operating a steam turbine.
  • the turbomachine has an outer housing has in which a rotor with three blade areas is rotatably supported, wherein one of the blade areas an inner Area is and the other outer areas are through which operate a flow medium along a respective one Flow direction flows, the inner blade area enclosed by the outer blade areas along the rotor is and the flow directions in the outer Bucket areas opposite to each other and from the inside Blade area are directed away.
  • This configuration takes advantage for the first time, that by the arrangement of the blade areas described above an outflowing flow medium with almost identical parameters such as pressure, temperature and volume flow exits at the outer housing ends. Because of the low Exit parameter of the steam is at the two ends of the housing the arrangement of sealing shell systems with Sealing shell steam return to the blading area not mandatory. One asymmetrical on the circumference of the case Warming by sealing shell steam introduction is locked out.
  • the compact design of the fluid machine leads to more Advantages in manufacturing that save material and time to lead.
  • the material and time can be saved among other things on a reduced version of the components Return shape.
  • the use of less material leads to components of lower mass and thus to better ones Start-up and operating behavior, especially the downsizing the last blade stages is advantageous here.
  • the flow medium is reduced Flow through the inner blade area via a return flow channel separated into two streams. One of the partial streams flows through the return flow channel.
  • the axial compensator can, for example consist of a bellows or similar.
  • the rotor is designed with a shaft shoulder attached in front of the first blade area.
  • a major advantage here is the simple, cost-effective integration in the housing.
  • the turbomachine preferably has an inflow area in which the flow medium in a subsequent expansion area is relaxed by a control level.
  • the Pressure of the flow medium in the expansion area is determined by relaxed a control level to a wheel space pressure.
  • the turbomachine can advantageously be designed as Axial compressor.
  • the object of the method is achieved according to the invention solved by the description of a method of operation a steam turbine.
  • the steam turbine is with a rotary bearing Rotor with three blade areas, one of which the blade area is an inner area and the others are external areas through which a fluid flows during operation along a respective flow direction flows, with the inner blade area from the outer Blade areas along the rotor is included and the flow medium after flowing through the inner blade area is divided into two sub-streams. After the split in. the two partial flows flows through one partial flow an outer blade area, and the other partial flow through the other blade area.
  • Fig. 1 shows a schematic longitudinal section through a Turbomachine 1 with an outer housing 2, a plurality of inner housings 11, 12, 16, 21 and a rotor 3.
  • On the rotor 3 four blade regions 4, 5, 6, 7 are arranged.
  • the four Blade areas are in this embodiment in two inner 5, 6 and two outer blade areas 4, 7 divided.
  • the two outer blade regions 4, 7 are in relation to one another arranged in opposite directions and point from the inner Blade areas 5, 6 away.
  • an inflow opening 8 is contained in the outer housing.
  • a control stage 9 is attached. After control level 9 follows in the direction of the first inner blade area 5 an expansion area 31.
  • first inner blade area 5 guide vanes 10 attached to the inner housing 11. Another follows on the first inner blade area 5 inner blade area 6.
  • second inner blade area 6 are further guide vanes 13 on a further inner housing 12 attached.
  • first inner blade area 5 is further guide vanes 13 on a further inner housing 12 attached.
  • second inner blade area 6 and an outer blade area 7 are one or contain multiple outlet openings 14.
  • On the outer blade area 7 are further guide vanes 15 on a further inner housing 16 fixed.
  • the return flow channel 19 is equipped with an axial compensator 22 thermal stresses between the return flow channel 19 and the outer housing 2 compensate.
  • the rotor 3 is designed with a shaft shoulder 23 to the Compensate axial thrust of the rotor 3.
  • sealing shells between the rotor 3 and the outer housing 2 24a and 24b arranged to leak from the fluid machine to reduce.
  • a flow medium flows through the inflow opening 8 into the fluid machine 1. From there, the fluid flows to control level 9, where the pressure on you Wheel space pressure is relaxed. The flow medium then flows through the first blade area 5. In the illustrated The exemplary embodiment then flows the flow medium through the second blade area 6. After this second Blade area 6 is the flow medium by means of a or several openings 14 separated into two partial streams 18, 33.
  • the Partial stream 33 flows through the outer blade area 7 the second partial flow 18 flows into the return flow channel 19 Inflow opening 32. From there, the partial flow flows through the further outer blade area 4. Both partial flows arrive after the flow through the outer blade regions 4, 5 via Outlet openings 17a, 17b from the turbomachine 1.
  • the individual partial flows of the separated flow medium reach the outer blade areas 4, 7 with almost identical parameters such as pressure, temperature and volume flow.
  • One advantage is the symmetrical heating of the housing.
  • the low state variables of the flow medium in these areas result in lower thermal deformations and the operational reliability of the turbomachine increases. It is advantageous to design sealing shells between the outer housing and the rotor in order to reduce the leakage without returning sealing shell steam between the blading areas.
  • the compact, single-case design creates more Advantages in production and in start-up and operating behavior. This takes advantage of the fact that material is saved can. In particular, the last blade stages can be in smaller Sizes are manufactured.
  • the fluid machine run as a steam turbine and secondly as Axial compressor.
  • Bucket areas 4, 5, 6 and 7 compresses and passes through a Line 27a highly compressed to an outlet 25a.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Control Of Positive-Displacement Air Blowers (AREA)
EP02002719A 2002-02-06 2002-02-06 Turbomachine avec des aubages à haute pression et basse pression Expired - Lifetime EP1335110B1 (fr)

Priority Applications (6)

Application Number Priority Date Filing Date Title
EP02002719A EP1335110B1 (fr) 2002-02-06 2002-02-06 Turbomachine avec des aubages à haute pression et basse pression
DE50209157T DE50209157D1 (de) 2002-02-06 2002-02-06 Strömungsmaschine mit Hochdruck- und Niederdruck-Schaufelbereich
ES02002719T ES2278821T3 (es) 2002-02-06 2002-02-06 Turbomaquina con regiones de paletas de alta presion y de baja presion.
JP2003021454A JP2003239704A (ja) 2002-02-06 2003-01-30 高圧部と低圧部とを備えた流体機械
US10/359,229 US6851927B2 (en) 2002-02-06 2003-02-06 Fluid-flow machine with high-pressure and low-pressure regions
CNB031025021A CN1313704C (zh) 2002-02-06 2003-02-08 带有高压和低压区段的流体机械和一种汽轮机的运行方法

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP02002719A EP1335110B1 (fr) 2002-02-06 2002-02-06 Turbomachine avec des aubages à haute pression et basse pression

Publications (2)

Publication Number Publication Date
EP1335110A1 true EP1335110A1 (fr) 2003-08-13
EP1335110B1 EP1335110B1 (fr) 2007-01-03

Family

ID=27589083

Family Applications (1)

Application Number Title Priority Date Filing Date
EP02002719A Expired - Lifetime EP1335110B1 (fr) 2002-02-06 2002-02-06 Turbomachine avec des aubages à haute pression et basse pression

Country Status (6)

Country Link
US (1) US6851927B2 (fr)
EP (1) EP1335110B1 (fr)
JP (1) JP2003239704A (fr)
CN (1) CN1313704C (fr)
DE (1) DE50209157D1 (fr)
ES (1) ES2278821T3 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
ITMI20101599A1 (it) * 2010-09-03 2012-03-04 Alstom Technology Ltd Impianto turbina a vapore

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN100340740C (zh) * 2004-09-17 2007-10-03 北京全三维动力工程有限公司 一种超高压冲动式汽轮机
NZ584908A (en) * 2007-10-04 2012-10-26 Stephen Mark West Turbine assembly with plural blades of different diameter in reversed orientation
CN102444426B (zh) 2010-09-30 2015-05-27 阿尔斯通技术有限公司 改装汽轮机的方法
JP5615150B2 (ja) * 2010-12-06 2014-10-29 三菱重工業株式会社 原子力発電プラントおよび原子力発電プラントの運転方法
DE102014224283A1 (de) * 2014-11-27 2016-06-02 Robert Bosch Gmbh Verdichter mit einem Dichtkanal
CN104963728B (zh) * 2015-06-25 2017-07-07 北京全三维能源科技股份有限公司 一种超高压冲动式汽轮机
JP7093238B2 (ja) * 2018-06-18 2022-06-29 三菱重工業株式会社 蒸気タービン設備及びコンバインドサイクルプラント
JP7134002B2 (ja) 2018-07-04 2022-09-09 三菱重工業株式会社 蒸気タービン設備及びコンバインドサイクルプラント

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB100369A (en) * 1915-04-28 1917-04-12 Oerlikon Maschf High Power and Speed Turbine Plant.
GB102741A (en) * 1915-12-15 1917-06-14 Oerlikon Maschf High Power Turbine Plant.
FR813337A (fr) * 1936-02-06 1937-05-31 Rateau Soc Dispositif pour rendre stable le fonctionnement des compresseurs rotatifs à rendement élevé
DE1919734A1 (de) * 1969-04-18 1970-11-05 Siemens Ag Dampfturbinenanlage
CH527364A (fr) * 1970-08-10 1972-08-31 Pellaux Roger Moteur à réaction, notamment pour aéronef
US4027996A (en) * 1974-07-22 1977-06-07 Kraftwerk Union Aktiengesellschaft Turbomachine, such as a steam turbine with high steam inlet temperature, especially

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1622805A (en) * 1924-02-08 1927-03-29 Bergmann Elek Citatswerke Ag Steam turbine
US2823891A (en) * 1953-05-20 1958-02-18 Westinghouse Electric Corp Steam turbine
US2796231A (en) * 1954-03-24 1957-06-18 Westinghouse Electric Corp High pressure steam turbine casing structure
JPS549641B2 (fr) * 1974-01-23 1979-04-26
US4362464A (en) * 1980-08-22 1982-12-07 Westinghouse Electric Corp. Turbine cylinder-seal system
FR2646466B1 (fr) * 1989-04-26 1991-07-05 Alsthom Gec Stator interne hp-mp unique de turbine a vapeur avec climatisation controlee
DE19700899A1 (de) * 1997-01-14 1998-07-23 Siemens Ag Dampfturbine

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB100369A (en) * 1915-04-28 1917-04-12 Oerlikon Maschf High Power and Speed Turbine Plant.
GB102741A (en) * 1915-12-15 1917-06-14 Oerlikon Maschf High Power Turbine Plant.
FR813337A (fr) * 1936-02-06 1937-05-31 Rateau Soc Dispositif pour rendre stable le fonctionnement des compresseurs rotatifs à rendement élevé
DE1919734A1 (de) * 1969-04-18 1970-11-05 Siemens Ag Dampfturbinenanlage
CH527364A (fr) * 1970-08-10 1972-08-31 Pellaux Roger Moteur à réaction, notamment pour aéronef
US4027996A (en) * 1974-07-22 1977-06-07 Kraftwerk Union Aktiengesellschaft Turbomachine, such as a steam turbine with high steam inlet temperature, especially

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
ITMI20101599A1 (it) * 2010-09-03 2012-03-04 Alstom Technology Ltd Impianto turbina a vapore
US8525362B2 (en) 2010-09-03 2013-09-03 Alstom Technology Ltd Steam turbine plant

Also Published As

Publication number Publication date
US20030175117A1 (en) 2003-09-18
EP1335110B1 (fr) 2007-01-03
CN1436918A (zh) 2003-08-20
US6851927B2 (en) 2005-02-08
JP2003239704A (ja) 2003-08-27
DE50209157D1 (de) 2007-02-15
ES2278821T3 (es) 2007-08-16
CN1313704C (zh) 2007-05-02

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