WO2014009333A1 - Segment d'entrée pour une turbomachine - Google Patents

Segment d'entrée pour une turbomachine Download PDF

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Publication number
WO2014009333A1
WO2014009333A1 PCT/EP2013/064429 EP2013064429W WO2014009333A1 WO 2014009333 A1 WO2014009333 A1 WO 2014009333A1 EP 2013064429 W EP2013064429 W EP 2013064429W WO 2014009333 A1 WO2014009333 A1 WO 2014009333A1
Authority
WO
WIPO (PCT)
Prior art keywords
inflow
segment
rotor
housing
turbomachine
Prior art date
Application number
PCT/EP2013/064429
Other languages
German (de)
English (en)
Inventor
Ingo Förster
Christian Musch
Uwe Zander
Original Assignee
Siemens Aktiengesellschaft
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 Aktiengesellschaft filed Critical Siemens Aktiengesellschaft
Priority to EP13739171.0A priority Critical patent/EP2859192B1/fr
Priority to IN10499DEN2014 priority patent/IN2014DN10499A/en
Priority to KR20157003409A priority patent/KR20150036474A/ko
Priority to US14/413,310 priority patent/US20150159486A1/en
Priority to CN201380037173.4A priority patent/CN104471193B/zh
Priority to JP2015520948A priority patent/JP5985748B2/ja
Publication of WO2014009333A1 publication Critical patent/WO2014009333A1/fr

Links

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
    • F01D3/00—Machines or engines with axial-thrust balancing effected by working-fluid
    • F01D3/02—Machines or engines with axial-thrust balancing effected by working-fluid characterised by having one fluid flow in one axial direction and another fluid flow in the opposite direction
    • 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
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • 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
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • 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
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • 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
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • 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
    • 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
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2220/00—Application
    • F05B2220/30—Application in turbines
    • F05B2220/301—Application in turbines in steam turbines

Definitions

  • the invention relates to a turbomachine comprising a rotor rotatably supported about a rotation axis, rotor blades disposed on the rotor, a casing disposed around the rotor, vanes disposed on the casing, a flow passage interposed between is formed of the rotor and the housing, an inflow, which is arranged in the housing and is designed for the inflow of steam, an inflow segment, which is arranged in the housing, inflow segment guide vanes, which are arranged in the inflow segment.
  • Turbomachines such as Steam turbines are used for example in the energy supply.
  • such turbomachines comprise a rotatably mounted rotor and a housing arranged around the rotatably mounted rotor.
  • the housing is divided into an inner housing and an outer housing arranged around the inner housing.
  • the rotors of such engineered turbomachines include blades that are disposed between vanes disposed on the inner shell and form a flow passage through which a flow medium flows.
  • steam is the flow medium.
  • the flow medium flowing into a turbomachine has comparatively high temperatures. So is at
  • the steam heated so that the steam may have temperatures of about 600 C.
  • Such high temperatures lead to high thermal loads on the turbomachine.
  • the components of the turbomachine are thermally loaded, which are arranged in the inflow region of the flow medium.
  • the rotor is also very special the point at which flows the flow medium in the turbomachine particularly thermally stressed. The materials must be chosen suitably so that the turbomachine can be operated.
  • An essential feature here is that bores are carried out, which are arranged in the inflow segment and produce a fluidic connection between the inflow and a relief space, which is arranged between the inflow segment and the rotor.
  • the bores are designed in such a way that a part of an inflow steam is guided through the bores and part of the inflow steam through the inflow segment vanes.
  • the inflow segment has a hub-side ring segment, in which the bores are formed.
  • the bores are seen in the flow direction of the inflow vapor upstream of the inflow segment guide. arranged shovels. As a result, a portion of the steam can be discharged directly before flowing through the inflow ring. This allows better cooling.
  • the bores are inclined at an angle a which is between 40 ° and 80 ° with respect to a radial direction passing through the axis of rotation. As a result, optimal cooling effects can be achieved, since the swirl of the steam flowing in under the inflow segment is essential for the most effective possible cooling.
  • six bores are formed, the number being influenced by the respective geometry, thermodynamics and height of the desired cooling effect.
  • Figure 1 is a schematic sectional view through a part of a turbomachine
  • Figure 2 is a partial perspective view of an inflow ring
  • Figure 3 is a sectional view through the inflow ring.
  • FIG. 1 shows a section of a turbomachine.
  • the turbomachine shown in FIG. 1 is designed as a steam turbine 1.
  • the steam turbine 1 has a rotor 3 rotatably mounted about a rotation axis 2.
  • the rotor 3 has different diameters.
  • blades 5 are arranged on a rotor surface 4 .
  • the rotor blade 5 has a blade root 6, which in a corresponding rotor groove 7 is arranged.
  • the rotor material immediately adjacent to the blade root 6 is also referred to as a blade claw.
  • an inner housing 8 is arranged in the rotor 3.
  • an outer housing 9 is arranged. Between the
  • Inner housing 8 and the outer housing 9, a sealing element 10 is arranged.
  • the inner housing 8 is formed such that an inflow 11 is formed by a steam supply, not shown. By this inflow 11 is fresh steam, which may have temperatures of up to 650 ° C or more supplied.
  • the inner housing 8 also carries guide vanes 12, which are arranged via guide blade feet 13 in corresponding inner housing grooves 14.
  • a flow channel 15 is formed, which is formed by the guide vanes 12 and blades 5.
  • the rotor 3 is formed with a thrust balance piston 16 having a substantially larger diameter. Between the surface 17 of the thrust balance piston 16 and the thrust balance piston 16
  • Inner housing 8 a shaft seal 18 is formed. Seen in the direction of rotation in front of the thrust balance piston 16, the rotor 2 has a smaller diameter, wherein in this section a second shaft seal 19 is arranged.
  • the inflow 11 is provided for the flow of steam and designed accordingly.
  • the inner housing 8 has in this area a projection 20 on which an inflow segment 21 is arranged.
  • the inflow segment 21 is essentially borrowed as a ring and installed in the inner housing 8. At the outer diameter of the inflow segment 21, the inflow segment 21 is fitted in a groove 22.
  • the inflow segment 21 has a hub-side ring segment 23 which is connected to the inner housing 8 via a second sealing element 24.
  • the hub-side ring segment 23 has a sealing groove 25 into which the second sealing element 24 is fitted. Furthermore, the inner housing 8 also has a groove 26 in which the other end of the second sealing element 24 is arranged.
  • the inflow segment 21 has inflow segment vanes 27 integrally formed with the inflow segment 21.
  • the rotor 3 is formed with a relief groove 28, which is characterized essentially by a smaller diameter and has a certain radial distance from the inflow segment 21 in order to form the relief space 30.
  • the inflow segment 21 in the installed state ensures a technically vapor-tight separation of the inflow channel 11 to the relief space 30 via the sealing elements and installation situation.
  • Holes 29 are arranged in the hub-side ring segment 23 in the inflow segment 21. These holes 29 establish a fluidic connection between the inflow 11 and a relief space 30, which is formed between the inflow segment 21 and the rotor 3.
  • a mass flow (M tot ) flows into the inflow 11.
  • This mass flow is divided into a smaller mass flow (Mi), which passes through the bores 29 and enters the discharge space 30 and a larger mass flow (M 2 ) passing through the inflow segment vane 27 flows and thereafter passes through the flow channel 15.
  • M ges Mi + Mi, where Mi ⁇ M 2 .
  • the mass flow Mi which leads through the bores 29, is divided into a mass flow M n , which passes via the second shaft seal 19 into a thrust balance piston chamber 33.
  • Another part of the mass flow Mi passes as a second mass flow M i2 along the hub-side ring segment 23 into the flow channel 15.
  • the mass flow M n + M i2 has a comparatively lower temperature than that of M tot and therefore leads to a cooling of the rotor surface in the relief groove 28.
  • the bores 29 are seen in the flow direction 32 of the inflow upstream of the inflow segment guide vanes 27.
  • FIG. 2 shows a partial view of the inflow segment 21.
  • a view from the rotation axis 2 takes place in the radial direction to the outside.
  • multiple inflow segment vanes 27 can be seen.
  • the hub-side ring segment 23 is substantially triangular in shape and has the groove 25 for receiving the sealing element 24.
  • FIG. 2 shows a perspective of the inflow element 21, wherein an inside surface 33 of the hub-side ring segment 23 can be seen.
  • the outlet 34 of the holes 29 is formed on this inside surface 33.
  • FIG. 3 shows a sectional view through the inflow segment 21.
  • only one inflow segment vane is designated by the reference numeral 27.
  • six holes 29 are executed, which are formed in a tangential direction to the discharge space 30 at an angle ⁇ .
  • the direction of rotation of the rotor 3 is counterclockwise.
  • the angle ⁇ is explained at the bore 29 in the twelve o'clock position.
  • a reference line 35 is shown in the radial direction.
  • a bore 29 is executed. Through this hole 29, the mass flow Mi flows.
  • the steam undergoes a speed change and thus a lowering of the static temperature of the steam relative to the rotating system, which then leads to a cooling of the surface of the rotor 3 with respect to the temperature of the mass flow M tot .

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

Turbomachine comportant un segment d'entrée (21) qui porte une aube directrice (27), et des trous (29), une partie du flux massique (M) parvenant par ces trous (29) jusqu'à une chambre de décharge (30) et entraînant un refroidissement.
PCT/EP2013/064429 2012-07-12 2013-07-09 Segment d'entrée pour une turbomachine WO2014009333A1 (fr)

Priority Applications (6)

Application Number Priority Date Filing Date Title
EP13739171.0A EP2859192B1 (fr) 2012-07-12 2013-07-09 Segment d'entrée de flux pour une turbomachine
IN10499DEN2014 IN2014DN10499A (fr) 2012-07-12 2013-07-09
KR20157003409A KR20150036474A (ko) 2012-07-12 2013-07-09 터보 기계의 유입 세그먼트
US14/413,310 US20150159486A1 (en) 2012-07-12 2013-07-09 Inflow segment for a turbomachine
CN201380037173.4A CN104471193B (zh) 2012-07-12 2013-07-09 用于流体机械的流入区段
JP2015520948A JP5985748B2 (ja) 2012-07-12 2013-07-09 ターボ機械のための流入セグメント

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP12176161.3A EP2685051A1 (fr) 2012-07-12 2012-07-12 Segment d'entrée de flux pour une turbomachine
EP12176161.3 2012-07-12

Publications (1)

Publication Number Publication Date
WO2014009333A1 true WO2014009333A1 (fr) 2014-01-16

Family

ID=48803516

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2013/064429 WO2014009333A1 (fr) 2012-07-12 2013-07-09 Segment d'entrée pour une turbomachine

Country Status (8)

Country Link
US (1) US20150159486A1 (fr)
EP (2) EP2685051A1 (fr)
JP (1) JP5985748B2 (fr)
KR (1) KR20150036474A (fr)
CN (1) CN104471193B (fr)
IN (1) IN2014DN10499A (fr)
PL (1) PL2859192T3 (fr)
WO (1) WO2014009333A1 (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102017114608A1 (de) * 2017-06-30 2019-01-03 Man Diesel & Turbo Se Turbinenzuströmgehäuse einer Axialturbine eines Turboladers

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2294983A (en) * 1941-04-29 1942-09-08 Westinghouse Electric & Mfg Co Steam turbine apparatus
US3429557A (en) * 1966-06-30 1969-02-25 Gen Electric Steam turbine rotor cooling arrangement
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
EP2343443A2 (fr) * 2010-01-12 2011-07-13 Kabushiki Kaisha Toshiba Turbine à vapeur

Family Cites Families (7)

* 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
US4242041A (en) * 1979-01-15 1980-12-30 Westinghouse Electric Corp. Rotor cooling for double axial flow turbines
JPS59153901A (ja) * 1983-02-21 1984-09-01 Fuji Electric Co Ltd 蒸気タ−ビンロ−タの冷却装置
JPH0734808A (ja) * 1993-07-26 1995-02-03 Mitsubishi Heavy Ind Ltd 蒸気タービン
JPH0742508A (ja) * 1993-08-02 1995-02-10 Mitsubishi Heavy Ind Ltd 蒸気タービンのロータ冷却装置
JP2004197696A (ja) * 2002-12-20 2004-07-15 Kawasaki Heavy Ind Ltd 旋回ノズルを備えたガスタービン
CN100378308C (zh) * 2006-07-07 2008-04-02 姜伟 叶轮加压转子喷射式燃气轮机

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2294983A (en) * 1941-04-29 1942-09-08 Westinghouse Electric & Mfg Co Steam turbine apparatus
US3429557A (en) * 1966-06-30 1969-02-25 Gen Electric Steam turbine rotor cooling arrangement
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
EP2343443A2 (fr) * 2010-01-12 2011-07-13 Kabushiki Kaisha Toshiba Turbine à vapeur

Also Published As

Publication number Publication date
CN104471193A (zh) 2015-03-25
EP2859192B1 (fr) 2016-05-25
IN2014DN10499A (fr) 2015-08-21
JP2015522130A (ja) 2015-08-03
EP2685051A1 (fr) 2014-01-15
KR20150036474A (ko) 2015-04-07
PL2859192T3 (pl) 2016-11-30
CN104471193B (zh) 2016-08-24
EP2859192A1 (fr) 2015-04-15
JP5985748B2 (ja) 2016-09-06
US20150159486A1 (en) 2015-06-11

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