EP1335110B1 - 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
EP1335110B1
EP1335110B1 EP02002719A EP02002719A EP1335110B1 EP 1335110 B1 EP1335110 B1 EP 1335110B1 EP 02002719 A EP02002719 A EP 02002719A EP 02002719 A EP02002719 A EP 02002719A EP 1335110 B1 EP1335110 B1 EP 1335110B1
Authority
EP
European Patent Office
Prior art keywords
region
blade
flow
regions
rotor
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
EP02002719A
Other languages
German (de)
English (en)
Other versions
EP1335110A1 (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 ES02002719T priority Critical patent/ES2278821T3/es
Priority to DE50209157T priority patent/DE50209157D1/de
Priority to EP02002719A priority patent/EP1335110B1/fr
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 turbomachine having a housing with a rotatably mounted rotor with three blade areas, which are fluidically connected. It further relates to a method for operating the aforementioned turbomachine as a steam turbine.
  • turbomachines which have a high-pressure steam and low-pressure steam region can be constructed in a one-piece or two-chambered manner.
  • 1997P03012 DE such turbomachines, in particular steam turbines are shown.
  • the two-part design does not belong to the technical field of the present invention and is therefore not further illustrated.
  • the housed design consists of a rotor with two single-flow blade areas facing the respective housing ends.
  • One vane area is designed as a high pressure steam vane area and another vane area as a low pressure steam area.
  • Incoming live steam initially flows in the axial direction through the blade area of the high-pressure steam blade area. From there, the now partially relaxed steam passes via a line to the medium-pressure steam blade area.
  • GB 100 369 describes a steam turbine comprising a medium-pressure turbine section, a low-pressure section turbine and a further low-pressure section turbine.
  • the flow medium flowing through the medium-pressure turbine section divides into two partial flows after flowing through, of which one partial flow flows through the first low-pressure turbine section and the other partial flow flows within the steam turbine to the further low-pressure section turbine.
  • This steam turbine is designed in such a way that the temperature of the flow medium before entry into the first low-pressure turbine part is higher than before entry into the second low-pressure turbine part.
  • the specific volume increases at a constant mass flow in the course of expansion relatively low. From the transition region between medium pressure and low pressure (about 2 to 3 bar), the specific volume of vapor increases sharply, the volume flow and thus the required flow area also. The realization of the flow area encounters physical limits (eg strength) and requires a large construction cost.
  • a disadvantage of these known embodiments with high-pressure expansion region is the concern of superheated steam at the interior of a turbine end.
  • the high energy vapor between the shells is partially recycled to lower temperature blading areas for thermodynamic process optimization.
  • the sealing cup steam introduction into the blading areas leads to casing asymmetry which is asymmetrical on the circumference of the casing, which results in thermal stresses and deformations, i. a distortion of the housing, which may possibly lead to a brushing of blades on the housing.
  • the object of the present invention is to design a single-flow turbomachine in such a way that no return of sealing shell steam is necessary with regard to thermodynamic process optimization.
  • Another object of the present invention is to provide a method of operating a steam turbine.
  • the turbomachine-type object is achieved in that the turbomachine has an outer housing in which a rotor with three blade areas is rotatably mounted, wherein one of the blade areas is an inner area in the axial direction and the other areas are outer areas, as seen in the axial direction wherein, in operation, a flow medium flows along a respective flow direction, the inner blade region being trapped by the outer blade regions along the rotor and the flow directions in the outer blade regions being opposite each other and facing away from the inner blade region, and the flow medium after flowing through the inner blade region is separable with a return passage so that a part of the flow medium flows through an outer blade portion and a second part through the other outer blade portion, wherein that the discoursegeh use has an inlet opening between the outer blade region and the inner blade region and the outer casing between the inner blade region and the other outer blade region has an outlet opening, wherein the outlet port is connected to the inlet opening via the backflow passage fluidically to each other.
  • the compact design of the turbomachine leads to further advantages in the production, which lead to material and time savings.
  • the material and time savings can be attributed, inter alia, to a design of the components in a reduced form.
  • the use of less material leads to components of lower mass and thereby to better starting and operating behavior, in particular the reduction of the last blade stages is advantageous here.
  • the axial compensator may for example consist of a bellows or the like.
  • the impact of the flow medium on the rotating blade regions leads to an acting in the axial direction Force.
  • This force is called axial thrust.
  • the rotor is designed with an attached in front of the first blade portion shaft paragraph in an advantageous embodiment. A significant advantage arises from the simple cost-effective integration in the housing.
  • the turbomachine preferably has an inflow region, in which the flow medium is expanded in a subsequent expansion region by a control stage.
  • the pressure of the flow medium in the expansion area is relieved by a control stage to a Radraumdruck.
  • the turbomachine can be advantageously carried out as axial compressor.
  • the object directed to the method is achieved according to the invention by the description of a method for operating a steam turbine.
  • the steam turbine having an outer casing is provided with a rotatably mounted rotor having three blade regions, wherein one of the blade regions is an inner region viewed in the axial direction and the other regions are outer regions through which a flow medium flows in a respective flow direction during operation. wherein the inner blade region is enclosed by the outer blade regions along the rotor and the flow medium is divided into two partial streams after flowing through the inner blade region.
  • the one sub-stream flows through an outer blade area, and the other sub-stream through the other blade area, wherein the flow medium through a arranged on the outer housing between the inner blade area and the other outer blade area outlet opening via a remindströmkanal to between the outer Blade region and the inner blade portion arranged inlet opening flows.
  • 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.
  • Four blade areas 4, 5, 6, 7 are arranged on the rotor 3.
  • the four blade areas are divided in this embodiment into two inner 5, 6 and two outer blade areas 4, 7.
  • the two outer blade regions 4, 7 are arranged opposite to one another and point away from the inner blade regions 5, 6.
  • an inflow opening 8 is contained in the outer housing.
  • a control stage 9 is attached.
  • an expansion region 31 follows in the direction of the first inner blade region 5.
  • 5 guide vanes 10 are attached to the inner casing 11 in the first inner blade region.
  • first inner blade area 5 On the first inner blade area 5 there follows a further inner blade area 6.
  • second inner blade area 6 In the second inner blade area 6, further guide blades 13 are attached to a further inner housing 12. Between the second inner blade area 6 and an outer blade area 7 are one or several outlet openings 14 included. At the outer blade area 7 more vanes 15 are fixed to a further inner housing 16.
  • an inflow opening 32 in the outer housing 2 is fluidically connected to the outlet opening 14 via a return flow channel 19.
  • inflow opening 32 in the outer housing 2 is fluidically connected to the outlet opening 14 via a return flow channel 19.
  • further guide vanes 20 in a further inner housing 21 are further guide vanes 20 in a further inner housing 21.
  • the return flow 19 is equipped with an axial compensator 22 to compensate for thermal stresses between the return flow 19 and the outer housing 2.
  • the rotor 3 is designed with a shaft shoulder 23 to compensate for the axial thrust of the rotor 3.
  • sealing shells 24a and 24b are arranged to reduce the leakage from the turbomachine.
  • a flow medium flows via the inflow opening 8 into the turbomachine 1. From there, the flow medium reaches the control stage 9, where the pressure is released to a Radraumtik. Thereafter, the flow medium flows through the first blade region 5. In the illustrated embodiment, the flow medium then flows through the second blade region 6. After this second blade region 6, the flow medium is separated into two partial streams 18, 33 by means of one or more openings 14. The partial flow 33 flows through the outer blade region 7. The second partial flow 18 flows via the return flow channel 19 into an inflow opening 32. From there, the partial flow flows through the further outer blade region 4. After the outer blade regions 4, 5 flow through, both partial flows reach via outlet openings 17a, 17b from the turbomachine 1.
  • the turbomachine can be designed as a steam turbine and, on the other hand, as an axial compressor.
  • superheated steam 26 passes via a feed line 27 into a steam turbine interior 28. After flowing through the previously described blade areas 4, 5, 6 and 7 in the steam turbine interior 28, the superheated steam is expanded and flows via a discharge 29 to a capacitor 30.
  • the rotation of the rotor 3 can be used to generate electrical energy.
  • the operating principle is as described below.
  • atmospheric air or the like is supplied in an inlet opening 30a via a feed line 29a into an axial compressor interior 28a.
  • the atmospheric air is compressed by a direction of rotation of the rotor 3 and thus of the previously described blade areas 4, 5, 6 and 7 in a direction opposite to that of the steam turbine, and reaches the outlet 25a in a highly compressed manner via a line 27a.

Claims (8)

  1. Turbomachine (1) ayant un fourreau (2) extérieur dans lequel est monté tournant un rotor (3) ayant trois aubages (4, 5, 6, 7), l'un des aubages étant, vu dans la direction axiale, un aubage (5, 6) intérieur et les autres étant, vu dans la direction axiale, des aubages (4, 7) extérieurs, dans lesquels en fonctionnement, un fluide en écoulement passe suivant une direction d'écoulement respective, l'aubage (5, 6) intérieur étant enfermés par les aubages (4, 7) extérieurs le long du rotor (3), les sens d'écoulement des aubages (4, 7) extérieurs étant opposés l'un à l'autre et s'éloignant de l'aubage (5, 6) intérieur, et le fluide en écoulement pouvant après avoir passé dans l'aubage (5, 6) intérieur, être séparé, par un canal(19) de retour, de façon à ce qu'une partie du fluide en écoulement passe dans un aubage (4) extérieur et qu'une deuxième partie du fluide passe par l'autre aubage (7) extérieur,
    caractérisée en ce que,
    le fourreau (2) extérieur a une ouverture (32) d'entrée entre l'aubage (4) extérieur et l'aubage (5, 6) intérieur et en ce que le fourreau (2) extérieur a une ouverture (14) de sortie entre l'aubage (5, 6) intérieur et l'autre aubage (7) extérieur, l'ouverture (14) de sortie communiquant du point de vue de la technique des fluides avec l'ouverture (32) d'entrée par le canal (19) de retour.
  2. Turbomachine suivant la revendication 1, caractérisée en ce que le canal (19) de retour est muni d'un compensateur (22) axial de compensation d'une dilatation thermique.
  3. Turbomachine (1) suivant l'une de revendications 1 à 2, caractérisée en ce que
    pour compenser un décalage axial, le rotor (3) est réalisé en ayant un épaulement (23) d'arbre ménagé en amont de l'aubage (5,6) intérieur.
  4. Turbomachine (1) suivant l'une de revendications 1 à 2, caractérisée en ce que
    pour réduire les fuites de la turbomachine (1), des coquilles (24a, 24b) d'étanchéité sont montées entre le rotor (3) et le fourreau (2) extérieur.
  5. Turbomachine (1) suivant l'une de revendications 1 à 4,ayant au moins une partie (8) d'admission du fluide en écoulement et une partie de détente se raccordant à la partie (8) d'admission,
    caractérisée en ce que la pression du fluide en écoulement dans la partie de détente peut être détendue jusqu'à une pression d'espace de roue par un étage (9) de régulation.
  6. Turbomachine (1) suivant l'une de revendications 1 à 5, caractérisée
    par une réalisation en turbine à vapeur.
  7. Turbomachine (1) suivant l'une de revendications 1 à 2, caractérisée par une réalisation en compresseur axial.
  8. Procédé pour faire fonctionner une turbine à vapeur ayant un fourreau (2) extérieur, qui est réalisé en ayant un rotor (3) monté tournant et ayant trois aubages (4, 5, 6, 7), dans lequel l'un des aubages (5, 6) est, vu dans la direction axiale, un aubage (5, 6) intérieur et les autres sont, vu dans la direction axiale, des aubages (4, 7) extérieurs, par lesquels un fluide en écoulement passe en fonctionnement suivant une direction d'écoulement, l'aubage (5, 6) intérieur étant enfermé le long du rotor(2) par les aubage (4, 7) extérieurs, dans lequel le fluide en écoulement est, après passage dans l'aubage (5, 6) intérieur subdivisé en deux sous-courants, l'un des sous courant passant dans un aubage (7) extérieur et l'autre sous courant dans l'autre aubage (4),
    caractérisé en ce que
    l'on fait passer le fluide en écoulement par une ouverture (14) de sortie disposée sur le fourreau (2) extérieur entre l'aubage (5, 6) intérieur et l'autre aubage (7) extérieur par un canal (19) de retour vers une ouverture (32) d'entrée disposée entre l'aubage (4) extérieur et l'aubage (5, 6) intérieur.
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
ES02002719T ES2278821T3 (es) 2002-02-06 2002-02-06 Turbomaquina con regiones de paletas de alta presion y de baja presion.
DE50209157T DE50209157D1 (de) 2002-02-06 2002-02-06 Strömungsmaschine mit Hochdruck- und Niederdruck-Schaufelbereich
EP02002719A EP1335110B1 (fr) 2002-02-06 2002-02-06 Turbomachine avec des aubages à haute pression et basse pression
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 EP1335110A1 (fr) 2003-08-13
EP1335110B1 true 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 (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11352912B2 (en) 2018-07-04 2022-06-07 Mitsubishi Power, Ltd. Steam turbine facility and combined cycle plant
US11359520B2 (en) 2018-06-18 2022-06-14 Mitsubishi Power, Ltd. Steam turbine facility and combined cycle plant

Families Citing this family (7)

* 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
US8358023B2 (en) * 2007-10-04 2013-01-22 Stephen Mark West Driving turbine blade assembly comprising a passage through which a fluid may pass
IT1402377B1 (it) * 2010-09-03 2013-09-04 Alstom Technology Ltd Impianto turbina a vapore
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

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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.
US1622805A (en) * 1924-02-08 1927-03-29 Bergmann Elek Citatswerke Ag Steam turbine
FR813337A (fr) * 1936-02-06 1937-05-31 Rateau Soc Dispositif pour rendre stable le fonctionnement des compresseurs rotatifs à rendement élevé
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
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
JPS549641B2 (fr) * 1974-01-23 1979-04-26
DE2435153B2 (de) * 1974-07-22 1977-06-30 Kraftwerk Union AG, 4330 Mülheim Turbomaschine, insbesondere dampfturbine mit hoher dampfeintrittstemperatur
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

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11359520B2 (en) 2018-06-18 2022-06-14 Mitsubishi Power, Ltd. Steam turbine facility and combined cycle plant
US11352912B2 (en) 2018-07-04 2022-06-07 Mitsubishi Power, Ltd. Steam turbine facility and combined cycle plant

Also Published As

Publication number Publication date
US20030175117A1 (en) 2003-09-18
CN1313704C (zh) 2007-05-02
US6851927B2 (en) 2005-02-08
DE50209157D1 (de) 2007-02-15
EP1335110A1 (fr) 2003-08-13
JP2003239704A (ja) 2003-08-27
CN1436918A (zh) 2003-08-20
ES2278821T3 (es) 2007-08-16

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