EP2685051A1 - Segment d'entrée de flux pour une turbomachine - Google Patents

Segment d'entrée de flux pour une turbomachine Download PDF

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Publication number
EP2685051A1
EP2685051A1 EP12176161.3A EP12176161A EP2685051A1 EP 2685051 A1 EP2685051 A1 EP 2685051A1 EP 12176161 A EP12176161 A EP 12176161A EP 2685051 A1 EP2685051 A1 EP 2685051A1
Authority
EP
European Patent Office
Prior art keywords
inflow
rotor
segment
housing
bores
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.)
Withdrawn
Application number
EP12176161.3A
Other languages
German (de)
English (en)
Inventor
Ingo Förster
Christian Musch
Uwe Zander
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 EP12176161.3A priority Critical patent/EP2685051A1/fr
Priority to EP13739171.0A priority patent/EP2859192B1/fr
Priority to PL13739171.0T priority patent/PL2859192T3/pl
Priority to PCT/EP2013/064429 priority patent/WO2014009333A1/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 EP2685051A1 publication Critical patent/EP2685051A1/fr
Withdrawn legal-status Critical Current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
    • 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 formed in the housing and the housing is arranged 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 define 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.
  • the steam is heated in such a way that the steam can have temperatures of more than 600 ° C.
  • Such high temperatures lead to large 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.
  • the invention has set itself the task of specifying an improved turbomachine.
  • 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 vanes arranged.
  • a portion of the steam can be discharged directly before flowing through the inflow ring. This allows better cooling.
  • the bores are inclined by an angle ⁇ which is between 40 ° and 80 ° with respect to a radial direction passing through the axis of rotation.
  • the FIG. 1 shows a section of a turbomachine.
  • turbomachine 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 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, which is formed substantially and depending on the design of an upper inner housing part and a lower inner housing part with horizontal parting or correspondingly from the left and right inner housing part with vertical parting line.
  • an outer housing 9 is arranged to the inner housing 8.
  • a sealing element 10 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 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 substantially formed 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.
  • 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 flows into the inflow 11.
  • This mass flow is divided into a smaller mass flow (M 1 ), which passes through the bores 29 and enters the discharge space 30 and into a larger mass flow (M 2 ), the flows through the inflow segment vane 27 and then passes through the flow channel 15.
  • M ges M 1 + M 1 , where M 1 ⁇ M 2 .
  • M 1 M 1 + M 1 , where M 1 ⁇ M 2 .
  • M 1 M 1 + M 1 , where M 1 ⁇ M 2 .
  • the mass flow M 1 which leads through the bores 29, into a mass flow M 11 , which passes through the second shaft seal 19 in a thrust balance piston antechamber 31.
  • Another part of the mass flow M 1 passes as a second mass flow M 12 on the hub-side ring segment 23 along in the flow channel 15th
  • the mass flow M 11 + M 12 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 holes 29 are seen in the flow direction 32 of the inflow steam, arranged in front of the inflow segment guide vanes 27.
  • the FIG. 2 shows a partial view of the inflow segment 21.
  • perspective shown takes a view from the axis of rotation 2 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.
  • the FIG. 2 shows a perspective of the inflow member 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.
  • inflow segment vane is designated by reference numeral 27.
  • six holes 29 are executed, which are formed in a tangential direction to the discharge chamber 30 at an angle ⁇ .
  • the direction of rotation of the rotor 3 is counterclockwise.
  • the angle ⁇ is explained on the bore 29 in the twelve o'clock position. From the axis of rotation 2 from a reference line 35 is shown in the radial direction. At an angle ⁇ , which is between 40 ° and 80 °, a bore 29 is executed. Through this bore 29, the mass flow M 1 flows . Due to the applied twist of the steam undergoes a change in velocity and thus a reduction in the static temperature of the steam relative to the rotating system, which then leads to a cooling of the surface of the rotor 3 relative 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)
EP12176161.3A 2012-07-12 2012-07-12 Segment d'entrée de flux pour une turbomachine Withdrawn EP2685051A1 (fr)

Priority Applications (9)

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
EP13739171.0A EP2859192B1 (fr) 2012-07-12 2013-07-09 Segment d'entrée de flux pour une turbomachine
PL13739171.0T PL2859192T3 (pl) 2012-07-12 2013-07-09 Segment wlotowy dla maszyny przepływowej
PCT/EP2013/064429 WO2014009333A1 (fr) 2012-07-12 2013-07-09 Segment d'entrée 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 (1)

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

Publications (1)

Publication Number Publication Date
EP2685051A1 true EP2685051A1 (fr) 2014-01-15

Family

ID=48803516

Family Applications (2)

Application Number Title Priority Date Filing Date
EP12176161.3A Withdrawn EP2685051A1 (fr) 2012-07-12 2012-07-12 Segment d'entrée de flux pour une turbomachine
EP13739171.0A Not-in-force EP2859192B1 (fr) 2012-07-12 2013-07-09 Segment d'entrée de flux pour une turbomachine

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP13739171.0A Not-in-force EP2859192B1 (fr) 2012-07-12 2013-07-09 Segment d'entrée de flux 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
WO2014009333A1 (fr) 2014-01-16
IN2014DN10499A (fr) 2015-08-21
JP2015522130A (ja) 2015-08-03
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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