US20150159486A1 - Inflow segment for a turbomachine - Google Patents

Inflow segment for a turbomachine Download PDF

Info

Publication number
US20150159486A1
US20150159486A1 US14/413,310 US201314413310A US2015159486A1 US 20150159486 A1 US20150159486 A1 US 20150159486A1 US 201314413310 A US201314413310 A US 201314413310A US 2015159486 A1 US2015159486 A1 US 2015159486A1
Authority
US
United States
Prior art keywords
turbomachine
rotor
bores
inflow segment
casing
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.)
Abandoned
Application number
US14/413,310
Other languages
English (en)
Inventor
Ingo Forster
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
Assigned to SIEMENS AKTIENGESELLSCHAFT reassignment SIEMENS AKTIENGESELLSCHAFT ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: Förster, Ingo, Musch, Christian, ZANDER, UWE
Publication of US20150159486A1 publication Critical patent/US20150159486A1/en
Abandoned legal-status Critical Current

Links

Images

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
    • 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
    • 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
    • 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, having a rotor which is mounted rotatably about an axis of rotation, rotor blades which are arranged on the rotor, a casing which is arranged about the rotor, guide vanes which are arranged on the casing, a flow duct which is formed between the rotor and the casing, a supply line which is arranged in the casing and is formed for supplying steam, an inflow segment which is arranged in the casing, inflow segment guide vanes which are arranged in the inflow segment.
  • Turbomachines such as steam turbines, are for example used for the supply of power.
  • Such turbomachines essentially comprise a rotatably mounted rotor and a casing arranged around the rotatably mounted rotor.
  • the casing is split into an inner casing and an outer casing arranged around the inner casing.
  • the rotors of turbomachines formed in this manner comprise rotor blades which are arranged between guide vanes arranged on the inner casing and which form a flow duct through which flows a flow medium.
  • steam is the flow medium.
  • the flow medium flowing into a turbomachine is at relatively high temperatures.
  • the steam is heated such that the steam can be at temperatures above 600° C.
  • Such high temperatures lead to high thermal loads on the turbomachine.
  • the components of the turbomachine which are subjected to particularly high thermal loading are those which are arranged in the inflow region of the flow medium.
  • the rotor is also subjected to particularly high thermal loading at the point at which the flow medium flows into the turbomachine. The choice of materials must be appropriate in order for the turbomachine to be operable.
  • the limits of use of a rotor are limited by this, since the thermal load is permissible and possible only up to a limit value.
  • the decisive strength parameters of the materials used yield disproportionately at excessive temperatures. From the temperature of the rotor material, it is possible to derive for example the maximum permissible shaft diameter, relative to the load on the shaft interior, or also the maximum permissible centrifugal forces in that region of rotors which is close to the rim, which in particular at 60 Hz applications can lead to limitation.
  • This inflow segment has a guide vane ring.
  • the fresh steam flowing into the turbomachine comes into contact first with the guide vanes of this inflow segment.
  • this inflow segment is arranged on the inner casing.
  • One physical effect which can be achieved with the inflow segment is that the fresh steam has increased swirl and thus leads to temperature-lowering effects of the inflow relief slot. This achieves a moderate cooling which reduces the thermal load on the first turbine blade roots and on the shaft interior.
  • Such inflow segments are also termed diagonal stages.
  • the invention has set itself an object of proposing an improved turbomachine.
  • An essential feature of this turbomachine is that bores are created which are arranged in the inflow segment and which establish a fluidic connection between the supply line and a relief space which is arranged between the inflow segment and the rotor.
  • the bores are formed such that part of the supply steam is fed through the bores and part of the supply steam is fed through the inflow segment guide vanes.
  • the inflow segment has a hub-side ring segment in which are formed the bores.
  • the bores are arranged upstream of the inflow segment guide vanes, as seen in the flow direction of the supply steam. It is thus possible for part of the steam to be diverted immediately before it flows through the inflow ring. This makes improved cooling possible.
  • the bores are inclined, with respect to a radial direction through the axis of rotation, by an angle ⁇ of between 40° and 80°. It is thereby possible to achieve optimum cooling effects since the swirl of the steam flowing in beneath the inflow segment is essential for the most effective possible cooling.
  • six bores are formed, wherein the number is influenced by the respective shape, thermodynamics and magnitude of the desired cooling effect.
  • FIG. 1 is a schematic section view through part of a turbomachine
  • FIG. 2 is a partial perspective view of an inflow ring
  • FIG. 3 is a section view through the inflow ring.
  • FIG. 1 shows a detail of a turbomachine.
  • the turbomachine shown in FIG. 1 is formed as a steam turbine 1 .
  • the steam turbine 1 has a rotor 3 which is mounted rotatably about an axis of rotation 2 .
  • the rotor 3 has various diameters.
  • Rotor blades 5 are arranged on a rotor surface 4 .
  • the rotor blade 5 has a rotor blade root 6 which is arranged in a corresponding rotor slot 7 .
  • the rotor material immediately adjacent to the rotor blade root 6 is also termed the rotor blade anchor.
  • an inner casing 8 which is essentially, and depending on the construction, formed from an upper inner casing part and a lower inner casing part, in the case of a horizontal parting joint, or in corresponding fashion is formed from a left inner casing part and a right inner casing part, in the case of a vertical parting joint.
  • An outer casing 9 is arranged around the inner casing 8 .
  • a sealing element 10 is arranged between the inner casing 8 and the outer casing 9 .
  • the inner casing 8 is formed such that a supply line 11 is formed by a steam supply, not shown in more detail. This supply line 11 supplies fresh steam which can be at temperatures of up to 650° C. or more.
  • the inner casing 8 also carries guide vanes 12 which are arranged in corresponding inner casing slots 14 via guide vane roots 13 .
  • a flow duct 15 which is formed by the guide vanes 12 and the rotor blades 5 , is created between the inner casing 8 and the rotor 3 .
  • the rotor 3 is formed with a thrust-equalizing piston 16 which has a substantially larger diameter.
  • a shaft seal 18 is formed between the surface 17 of the thrust-equalizing piston 16 and the inner casing 8 . Upstream of the thrust-equalizing piston 16 , as seen in the rotation direction, the rotor 2 has a smaller diameter, wherein a second shaft seal 19 is arranged in this section.
  • the supply line 11 is provided to supply steam and is formed accordingly.
  • the inner casing 8 has, in this region, a projection 20 against which an inflow segment 21 is arranged.
  • the inflow segment 21 is substantially formed as a ring and is installed in the inner casing 8 .
  • the inflow segment 21 is fitted into a slot 22 .
  • the inflow segment 21 has a hub-side ring segment 23 which is connected to the inner casing 8 via a second sealing element 24 .
  • the hub-side ring segment 23 has a sealing slot 25 into which the second sealing element 24 is fitted.
  • the inner casing 8 also has a slot 26 in which the other end of the second sealing element 24 is arranged.
  • the inflow segment 21 has inflow segment guide vanes 27 which are formed in one piece with the inflow segment 21 .
  • the rotor 3 is formed with a relief slot 28 which is essentially characterized by a smaller diameter and has a certain radial separation from the inflow segment 21 in order to form the relief space 30 .
  • the inflow segment 21 ensures, by means of the sealing elements and installation situation, a technical steam-tight separation of the supply duct 11 from the relief space 30 .
  • Bores 29 are arranged in the hub-side ring segment 23 in the inflow segment 21 . These bores 29 establish a fluidic connection between the supply line 11 and a relief space 30 which is formed between the inflow segment 21 and the rotor 3 .
  • a mass flow rate flows in the supply line 11 .
  • This mass flow rate splits into a smaller mass flow rate (M 1 ), which passes through the bores 29 and enters the relief space 30 , and a larger mass flow rate (M 2 ), which flows through the inflow segment guide vanes 27 and then passes through the flow duct 15 .
  • M ges M 1 +M 2 , where M 1 ⁇ M 2 .
  • the mass flow rate M 1 which passes through the bores 29 , splits into a mass flow rate M 11 , which enters a thrust-equalizing piston antechamber 31 via the second shaft seal 19 .
  • Another part of the mass flow rate M 1 passes along the hub-side ring segment 23 and into the flow duct 15 .
  • the mass flow rate M 11 +M 12 is at a lower temperature than M ges and thus contributes to cooling the rotor surface in the relief slot 28 .
  • the bores 29 are arranged upstream of the inflow segment guide vanes 27 , as seen in the flow direction 32 of the supply steam.
  • FIG. 2 shows a partial view of the inflow segment 21 .
  • the perspective shown in FIG. 2 shows a view outwards from the axis of rotation 2 , in the radial direction.
  • the perspective shown shows multiple inflow segment guide vanes 27 .
  • the hub-side ring segment 23 is essentially triangular in shape and has the slot 25 for receiving the sealing element 24 .
  • FIG. 2 shows a perspective of the inflow element 21 showing an inner surface 33 of the hub-side ring segment 23 .
  • the outlet 34 from the bores 29 is formed on this inner surface 33 .
  • FIG. 3 shows a section view through the inflow segment 21 .
  • the reference sign 27 For the sake of clarity, only one inflow segment guide vane is provided with the reference sign 27 .
  • six bores 29 are created, which are formed in a tangential direction to the relief space 30 , at the angle ⁇ .
  • the direction of rotation of the rotor 3 is counterclockwise.
  • the angle ⁇ is labeled by way of example on the bore 29 at the twelve o′clock position.
  • a reference line 35 is shown, proceeding in the radial direction from the axis of rotation 2 .
  • a bore 29 is created at an angle ⁇ of between 40° and 80°.
  • the mass flow rate M 1 flows through this bore 29 .
  • the imparted swirl changes the velocity of the steam, whereby the static temperature of the steam is lowered 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 rate M ges .

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)
US14/413,310 2012-07-12 2013-07-09 Inflow segment for a turbomachine Abandoned US20150159486A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP12176161.3A EP2685051A1 (de) 2012-07-12 2012-07-12 Einströmsegment für eine Strömungsmaschine
EP12176161.3 2012-07-12
PCT/EP2013/064429 WO2014009333A1 (de) 2012-07-12 2013-07-09 Einströmsegment für eine strömungsmaschine

Publications (1)

Publication Number Publication Date
US20150159486A1 true US20150159486A1 (en) 2015-06-11

Family

ID=48803516

Family Applications (1)

Application Number Title Priority Date Filing Date
US14/413,310 Abandoned US20150159486A1 (en) 2012-07-12 2013-07-09 Inflow segment for a turbomachine

Country Status (8)

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

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 (1)

* 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

Family Cites Families (10)

* 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
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
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
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
JP5558120B2 (ja) * 2010-01-12 2014-07-23 株式会社東芝 蒸気タービンのロータ冷却装置及びこの冷却装置を備えた蒸気タービン

Patent Citations (1)

* 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

Also Published As

Publication number Publication date
WO2014009333A1 (de) 2014-01-16
PL2859192T3 (pl) 2016-11-30
EP2685051A1 (de) 2014-01-15
JP2015522130A (ja) 2015-08-03
EP2859192A1 (de) 2015-04-15
EP2859192B1 (de) 2016-05-25
IN2014DN10499A (enExample) 2015-08-21
JP5985748B2 (ja) 2016-09-06
CN104471193A (zh) 2015-03-25
KR20150036474A (ko) 2015-04-07
CN104471193B (zh) 2016-08-24

Similar Documents

Publication Publication Date Title
US10808556B2 (en) Integrated strut and IGV configuration
US8092152B2 (en) Device for cooling slots of a turbomachine rotor disk
CN102128054A (zh) 汽轮机
US10724540B2 (en) Stator for a gas turbine engine fan
US20180230839A1 (en) Turbine engine shroud assembly
CN107923246B (zh) 用于蒸汽轮机的转子冷却
KR20140116115A (ko) 터빈 엔진을 위한 베어링 브라켓
KR101920693B1 (ko) 가스유입 방지를 위한 실링부재를 포함하는 터빈.
JP2011094616A (ja) タービン翼形部−側壁の一体化
CN102373972B (zh) 尖部流道轮廓
US20130330173A1 (en) Method for determining the diameter of a rotor, which is equipped with rotor blades, of a turbomachine
EP3249157B1 (en) Steam turbine
US20110164962A1 (en) Turbine blade with tip brush seal
US9574453B2 (en) Steam turbine and methods of assembling the same
US10370987B2 (en) Blade or vane row and gas turbine
US10041368B2 (en) Turbine assembly
EP3358142B1 (en) Turbine tip shroud leakage flow control
CN105358797A (zh) 用于涡轮机的转子
CN106574502B (zh) 蒸汽轮机和用于运行蒸汽轮机的方法
US20150159486A1 (en) Inflow segment for a turbomachine
JP6496534B2 (ja) 蒸気タービン及びその組み立て方法
JP2017057838A (ja) ガスタービン冷却構造およびガスタービン
JP2009191850A (ja) 蒸気タービンエンジンとその組立方法
US20130034445A1 (en) Turbine bucket having axially extending groove
RU2638250C2 (ru) Уплотнение для газотурбинного двигателя

Legal Events

Date Code Title Description
AS Assignment

Owner name: SIEMENS AKTIENGESELLSCHAFT, GERMANY

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:FOERSTER, INGO;MUSCH, CHRISTIAN;ZANDER, UWE;SIGNING DATES FROM 20141202 TO 20141205;REEL/FRAME:034653/0933

STCB Information on status: application discontinuation

Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION