EP1148208B1 - Turbine stator - Google Patents

Turbine stator Download PDF

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Publication number
EP1148208B1
EP1148208B1 EP01303458A EP01303458A EP1148208B1 EP 1148208 B1 EP1148208 B1 EP 1148208B1 EP 01303458 A EP01303458 A EP 01303458A EP 01303458 A EP01303458 A EP 01303458A EP 1148208 B1 EP1148208 B1 EP 1148208B1
Authority
EP
European Patent Office
Prior art keywords
rings
mentioned
cavities
blades
stator
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
EP01303458A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP1148208A3 (en
EP1148208A2 (en
Inventor
Giuseppe Ghelli
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.)
Nuovo Pignone Holding SpA
Nuovo Pignone SpA
Original Assignee
Nuovo Pignone Holding SpA
Nuovo Pignone SpA
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 Nuovo Pignone Holding SpA, Nuovo Pignone SpA filed Critical Nuovo Pignone Holding SpA
Publication of EP1148208A2 publication Critical patent/EP1148208A2/en
Publication of EP1148208A3 publication Critical patent/EP1148208A3/en
Application granted granted Critical
Publication of EP1148208B1 publication Critical patent/EP1148208B1/en
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
    • 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
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • F01D9/044—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators permanently, e.g. by welding, brazing, casting or the like
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/10—Manufacture by removing material
    • F05D2230/13—Manufacture by removing material using lasers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/22—Manufacture essentially without removing material by sintering
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators

Definitions

  • the present invention relates to a process for producing a stator diaphragm in a steam turbine or gas expander.
  • the present invention further relates to a stator diaphragm for steam turbine or gas expander.
  • steam turbines are machines supplied by vapour, generally water vapour, and suitable for converting into mechanical work part of the kinetic energy obtained following the expansion of the steam or of a previously compressed gas.
  • the previously superheated or saturated steam, or a compressed gas is caused to expand in the turbine by passing through several alternate stator and rotor stages.
  • the rotor stages are integral with the motor shaft to which they transmit the overall torque, whereas the stator stages serve to present the flow of steam or gas in suitable conditions at the inlet of the rotor blades.
  • the stator is constituted by a set of stator blades, between each pair of which a corresponding nozzle is located.
  • the current technique for constructing and mounting the stator parts of the steam turbines or gas expanders of known construction is based on the following machining cycle.
  • the blade is obtained from a drawn bar, cut to size and machined at the ends to create a coupling to the case and a pin for fixing the canopy.
  • the case has a C-shaped cavity inside which the blades are introduced circumferentially.
  • the pitch between the blades is ensured by a spacer heel which undergoes the same end machining as the blade for anchorage to the case.
  • Blades and heels are thus mounted alternately in a slot obtained on the case of the turbine.
  • An appropriately perforated ring is then mounted on the other end of the blade and its anchorage is ensured by the riveting of the pins of the blades on the ring.
  • EP-A-0 947 666 describes a high temperature soldering process which relies upon an external support for fixturing the blade ends.
  • US 3,909,157 contemplates a multi-part construction for a turbine-nozzle assembly.
  • EP-A-0 575 742 relates to the rotor wheel of a turbine with motor blades made from drawn profiled material which are inserted by at least one end into a holding plate provided with shaped cut-outs.
  • US 5,732,468 describes an airfoil and a band or platform member of a vane segment, such as of a turbine engine, which are bonded at a non-linear clearance slot formed between a shelf in the band and an end and edge of the airfoil.
  • GB-A-1 304 001 describes a stator blade assembly, for a fluid-flow machine such as a gas turbine engine, comprising a stator blade rigidly located in a slot in a stator blade ring 6.
  • US 5,332,360 describes a gas turbine engine stator vane which includes a groove extending laterally in an outer surface at one end thereof between leading and trailing edges for receiving a brazing material.
  • the object of the invention is therefore to provide a process for producing a stator diaphragm in a steam turbine or in a gas expander which permits a reduction of the construction and assembly time and the associated machining work, with consequent major financial advantages.
  • a further object of the invention is to provide a process for constructing and brazing stator diaphragms of steam turbines or gas expanders which enables construction errors to be substantially reduced.
  • Another object of the invention is to provide a process for constructing and brazing stator diaphragms of steam turbines or gas expanders which enables subsequent repair or replacement operations to be considerably simplified.
  • the present invention provides a process for producing a stator diaphragm in a steam turbine or gas expander, as claimed in claim 1.
  • the present invention provides a stator diaphragm for a steam turbine or gas expander, as claimed in claim 7.
  • the preparation phase of the rings is achieved by machining the rings separately by means of water jet cutting, for the purpose of obtaining the radial cavities having the profile of the blades, all with the aid of a numerically controlled machine tool.
  • the preparation phase of the cavities of the rings is achieved by cutting the cavities by laser.
  • the preparation phase of the cavities of the rings is achieved by cutting the cavities by electron discharge machining.
  • the brazing material in the form of paste, is inserted into the cavities having the profile of the blades.
  • the subsequent furnace brazing operation in vacuo promotes the penetration of the brazing material into the clearance between the profile of the blades and the said cavities.
  • the diaphragm subsequent to the brazing operation is machined according to the final dimensions and is cut into two half-rings by electron discharge machining for final mounting in the case of the above-mentioned steam turbine or the above-mentioned gas expander.
  • the present invention also relates to a stator diaphragm for steam turbine or for gas expander, characterized in that it comprises two rings, machined separately to obtain radial cavities having the profile of the blades and suitable for the subsequent housing of the above-mentioned blades, in which an appropriate quantity of brazing material, in the form of paste, is inserted in the above-mentioned cavities.
  • the assembly comprising the stator diaphragm, and the blades fixed thereto, is denoted overall by the reference numeral 10.
  • each blade 11 is fixed at the ends by two rings 12 and 13, so as to create a diaphragm 10.
  • each blade 11 is fixed to an internal ring 12 whereas another end of each blade 11 is fixed to an external ring 13.
  • the diaphragm 10 thus formed is then mounted in the case of the steam turbine, or of the gas expander, in which a cavity of rectangular cross-section has previously been produced.
  • the diaphragm 10 is thus obtained with two rings 12 and 13, preferably forged, which are machined separately with a water jet cutting process.
  • Cutting is carried out with a numerically controlled machine tool.
  • the cutting process may be carried out with laser or by means of electron discharge machining.
  • the blades 11 are always obtained from a drawn bar and are cut to size as previously carried out, but are not machined to have the upper cavity for anchoring them to the case and the pin at the other end is therefore no longer present.
  • the brazing material 14, 14' in the form of paste, is inserted into the cavities 15, 15' and into the clearance between the profile of the blades 11 and the cavities 15, 15' of the external 13 and internal 12 rings.
  • Brazing takes place in a furnace in vacuo, at controlled temperature, according to the parameters outlined below.
  • the blades 11 are fixed by making a small welding bead with welding material (on the internal side of the ring only) so as to ensure a stable position for the subsequent operations.
  • An auxiliary adhesive linen-finish tape for the injection of the brazing paste is applied to the external and internal diameter of the rings.
  • the brazing material in the form of paste 14 and 14' is then injected into the cavities 15 and 15' located on the rings from both the side of the internal 12 and external 13 diameter, care being taken to control the injection pressure so as to cause the paste 14, 14' to ascend as far as the limit of the corners of the edge of the slot facing the steam flow channel.
  • Brazing takes place in a furnace in vacuo at a pressure less than 5x10 -3 TORR.
  • the diaphragm 10 is machined according to the final dimensions and is then cut into two half-rings, by means of electron discharge machining by wire or laser.
  • the invention described above makes it possible to install, in a single diaphragm, two rings inside which the blades of the stator are rendered integral by brazing.
  • stator diaphragm 10 of the invention gives rise to only two elements to be handled, the upper half-ring and the lower half-ring, instead of all the blades 11 as in the systems according to the prior art.
  • the structural strength of the diaphragm is increased, and the manufacturing tolerances are also reduced, thanks also to the automation of the production process and the elimination of manual adjustments.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Diaphragms And Bellows (AREA)
  • Welding Or Cutting Using Electron Beams (AREA)
EP01303458A 2000-04-18 2001-04-12 Turbine stator Expired - Lifetime EP1148208B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
ITMI000870 2000-04-18
IT2000MI000870A IT1317277B1 (it) 2000-04-18 2000-04-18 Procedimento per la realizzazione di un diaframma statorico in unaturbina a vapore e diaframma statorico cosi' realizzato.

Publications (3)

Publication Number Publication Date
EP1148208A2 EP1148208A2 (en) 2001-10-24
EP1148208A3 EP1148208A3 (en) 2004-06-02
EP1148208B1 true EP1148208B1 (en) 2006-06-14

Family

ID=11444884

Family Applications (1)

Application Number Title Priority Date Filing Date
EP01303458A Expired - Lifetime EP1148208B1 (en) 2000-04-18 2001-04-12 Turbine stator

Country Status (8)

Country Link
EP (1) EP1148208B1 (enrdf_load_stackoverflow)
JP (1) JP2002038904A (enrdf_load_stackoverflow)
KR (1) KR100602283B1 (enrdf_load_stackoverflow)
CN (1) CN1316142C (enrdf_load_stackoverflow)
CZ (1) CZ299431B6 (enrdf_load_stackoverflow)
DE (1) DE60120549T2 (enrdf_load_stackoverflow)
IT (1) IT1317277B1 (enrdf_load_stackoverflow)
RU (1) RU2268371C2 (enrdf_load_stackoverflow)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7665531B2 (en) 1998-07-22 2010-02-23 Weatherford/Lamb, Inc. Apparatus for facilitating the connection of tubulars using a top drive

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6800829B1 (en) * 2003-05-29 2004-10-05 General Electric Company Method and apparatus for repairing air-cooled airfoils
FR2860740B1 (fr) * 2003-10-10 2007-03-02 Snecma Moteurs Procede de brasage d'un redresseur de compresseur de turbomachine.
US7303112B2 (en) * 2004-10-29 2007-12-04 United Technologies Corporation Repair of braze joint and article repaired
GB2436597A (en) 2006-03-27 2007-10-03 Alstom Technology Ltd Turbine blade and diaphragm
DE102008052602A1 (de) * 2008-10-21 2010-04-22 Siemens Aktiengesellschaft Swirler und Fertigungsverfahren für einen Swirler
ITCO20120014A1 (it) * 2012-04-06 2013-10-07 Nuovo Pignone Srl Anello di diaframma di pala statorica, turbina a vapore e metodo
CN104454028A (zh) * 2014-11-14 2015-03-25 东方电气集团东方汽轮机有限公司 提高汽轮发电机组采暖供热季节运行效率的方法
DE102016209210A1 (de) * 2016-05-27 2017-12-14 Schaeffler Technologies AG & Co. KG Hydrodynamischer Drehmomentwandler
CN109989791B (zh) * 2019-04-03 2021-11-26 大唐东营发电有限公司 一种汽轮机转子散热系统

Family Cites Families (15)

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Publication number Priority date Publication date Assignee Title
GB1304001A (enrdf_load_stackoverflow) * 1969-02-10 1973-01-24
US3909157A (en) * 1972-01-27 1975-09-30 Chromalloy American Corp Turbine nozzle-vane construction
CA1011177A (en) * 1973-12-14 1977-05-31 Wall Colmonoy Corporation Vacuum furnace brazing of superalloy parts
JPS5322141A (en) * 1976-08-13 1978-03-01 Kawasaki Steel Co Backing strap for oneeside welding
US4509238A (en) * 1983-03-21 1985-04-09 General Electric Company Method for fabricating a steam turbine diaphragm
DE4023912A1 (de) * 1990-07-27 1992-01-30 Zbigniew Pagacz Verfahren zur herstellung eines felgensterns
RU1825021C (ru) * 1991-01-30 1995-09-10 Научно-производственное предпри тие "Завод им.В.Я.Климова" Сопловой аппарат турбины
DE9207017U1 (de) * 1992-05-23 1992-09-03 ABB Patent GmbH, 6800 Mannheim Laufrad einer Turbine
JP3218800B2 (ja) * 1993-05-31 2001-10-15 石川島播磨重工業株式会社 タービン静翼の組み付け方法
US5332360A (en) * 1993-09-08 1994-07-26 General Electric Company Stator vane having reinforced braze joint
JPH08141737A (ja) * 1994-11-11 1996-06-04 Ogasawara Yoshihiro 鉄板または鉄骨の溶接方法
JPH08170502A (ja) * 1994-12-12 1996-07-02 Mitsubishi Heavy Ind Ltd ガスタービン静翼
US5732468A (en) * 1996-12-05 1998-03-31 General Electric Company Method for bonding a turbine engine vane segment
JP3559152B2 (ja) * 1997-10-13 2004-08-25 新潟原動機株式会社 ターボ機械の静翼及びその組立方法
DE19813958C1 (de) * 1998-03-28 1999-11-25 Mtu Muenchen Gmbh Verfahren zum Herstellen eines gebauten Leitkranzes einer Gasturbine, insbesondere eines Flugtriebwerkes, sowie ein nach dem Verfahren hergestellter Leitkranz

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7665531B2 (en) 1998-07-22 2010-02-23 Weatherford/Lamb, Inc. Apparatus for facilitating the connection of tubulars using a top drive

Also Published As

Publication number Publication date
EP1148208A3 (en) 2004-06-02
EP1148208A2 (en) 2001-10-24
ITMI20000870A0 (it) 2000-04-18
RU2268371C2 (ru) 2006-01-20
JP2002038904A (ja) 2002-02-06
ITMI20000870A1 (it) 2001-10-18
DE60120549T2 (de) 2007-06-06
CZ299431B6 (cs) 2008-07-23
KR100602283B1 (ko) 2006-07-14
IT1317277B1 (it) 2003-05-27
CN1316142C (zh) 2007-05-16
DE60120549D1 (de) 2006-07-27
CZ20011372A3 (cs) 2001-12-12
KR20010098577A (ko) 2001-11-08
CN1318686A (zh) 2001-10-24

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