EP2360351A1 - Lagerungsvorrichtung für die Welle einer Gasturbine - Google Patents

Lagerungsvorrichtung für die Welle einer Gasturbine Download PDF

Info

Publication number
EP2360351A1
EP2360351A1 EP11155903A EP11155903A EP2360351A1 EP 2360351 A1 EP2360351 A1 EP 2360351A1 EP 11155903 A EP11155903 A EP 11155903A EP 11155903 A EP11155903 A EP 11155903A EP 2360351 A1 EP2360351 A1 EP 2360351A1
Authority
EP
European Patent Office
Prior art keywords
bearing assembly
shaft
axis
supporting body
assembly according
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Withdrawn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
EP11155903A
Other languages
English (en)
French (fr)
Inventor
Gianluigi Bertino
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.)
Ansaldo Energia SpA
Original Assignee
Ansaldo Energia 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 Ansaldo Energia SpA filed Critical Ansaldo Energia SpA
Publication of EP2360351A1 publication Critical patent/EP2360351A1/de
Withdrawn legal-status Critical Current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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
    • F01D25/162—Bearing supports
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/003—Preventing or minimising internal leakage of working-fluid, e.g. between stages by packing rings; Mechanical seals
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
    • 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
    • F05D2250/00—Geometry
    • F05D2250/40—Movement of components
    • F05D2250/42—Movement of components with two degrees of freedom

Definitions

  • the present invention relates to a bearing assembly for a shaft of a gas turbine and to a gas turbine comprising said bearing assembly.
  • the present invention relates to a bearing assembly for a shaft of a gas turbine of an electric power plant.
  • a known type of gas turbine comprises a rotor section provided with a shaft extending along a longitudinal rotation axis, and a bearing assembly, which comprises a supporting structure, a bearing, which is arranged between the supporting structure and the shaft and which is supported by the supporting structure, and a sealing element, which is arranged between the supporting structure and the shaft at an end of the supporting structure.
  • the supporting structure is generally provided with alignment holes, which are used to fix the bearing assembly to the stator section of the gas turbine in a position aligned with the shaft.
  • the positioning and fixing operations of the bearing assembly take a long time.
  • the sealing element of the bearing assembly thus configured is subject to early deterioration during the transient steps in which the shaft is displaced, not guaranteeing correct sealing.
  • the shaft At rest, the shaft is lowered into the central portion by effect of its weight, while, when running, the shaft is subject to radial displacements mainly caused by thermal expansion phenomena.
  • the shaft is subjected to radial displacements such as to substantially describe an arch which extends about the rotation axis of the shaft.
  • the present invention relates to a bearing assembly for a shaft of a gas turbine in accordance with claim 1.
  • the invention relates to a gas turbine in accordance with claim 13.
  • a gas turbine is indicated with the reference number 1 (only one portion is shown in figure 1 for the sake of simplicity) comprising a rotor section 2, a stator section 3, and a bearing assembly 4.
  • the rotor section 2 rotates about a longitudinal rotation axis A and is provided with a shaft 5a, which comprises a plurality of rotor discs 5b (known and shown in part in the accompanying figures) and a tie rod 5c, which keeps the rotor discs 5b compacted during rotation about axis A.
  • the stator section 3 is fixed and supported by a supporting structure on the ground (not shown in the accompanying figures).
  • the bearing assembly 4 is arranged about the shaft 5a substantially at the exhaust of the gas turbine 1 and is coupled to the stator section 3.
  • the bearing assembly 4 comprises a supporting body 6, a bearing 7 (shown only in figures 2 and 3 ), which is arranged between the supporting body 6 and the shaft 5a and is supported by the supporting body 6, and a sealing element 8.
  • the supporting body 6 has a substantially cylindrical shape and extends about an axis B, coinciding in use with the rotation axis A of shaft 5a.
  • the supporting body 6 is coupled with the stator section 3 of the gas turbine 1.
  • the supporting body 6 is provided with two cylinders 10, which are coaxial and extend along an axis C orthogonal to axis B.
  • the cylinders 10 are arranged diametrically opposite on the middle plane and are adapted to engage respective seats 11 of the stator section 3 of the gas turbine 1.
  • the cylindrical coupling between the seats 11 and the cylinders 10 allows the bearing assembly 4 to rotate about axis C to follow the movements of the shaft 5a during operation of the gas turbine 1 (as shown by the arrow in figure 2 ).
  • the shape of the cylinders 10 is complementary to that of the respective seats 11, but undersized.
  • the cylinders 10 are housed in the respective seats 11 using shims 12 for adjusting the position of the supporting body 6 with respect to the shaft 5a so that the rotation axis A of the shaft 5a substantially coincides with axis B of the supporting body 6.
  • the shims 12 are fixed to the stator section 3.
  • the supporting body 6 is further provided with a cylinder 13, which extends along an axis D orthogonal to axis B and to axis C and adapted to engage a respective ring 14 of a plate 15, which slides in a respective seat 16 of the stator section 3 of the gas turbine 1.
  • the cylindrical coupling between the ring 14 of the plate 15 and cylinder 13 allows the bearing assembly 4 to turn about axis C (as shown by the arrow in figure 2 ) to follow the movements of the shaft 5a during operation of the gas turbine 1.
  • the seat 16 of the stator section 3 extends parallel to axis B and the plate 15 slides in the seat 16 parallel to axis B to allow the supporting body 6 to turn about axis C.
  • the shape of the cylinder 12 is not complementary with the seat 16, but is undersized.
  • the cylinder 13 is housed in the respective seat 16 using shims 17 for adjusting the position of the supporting body 6 with respect to the shaft 5a so that the rotation axis A of the shaft 5a substantially coincides with axis B of the supporting body 6.
  • the shims 17 are fixed to the stator section 3.
  • the bearing 7 is an oscillating slide bearing, which comprises five slides 18, arranged equidistant along the inner face of the bearing 7. Each slide 18 is free to move about a respective supporting pin 19.
  • the slides 18 follow the movement of the shaft 5a.
  • the sealing element 8 is supported by the supporting element 6 at an end of the supporting body 6 and extends about the shaft 5a.
  • sealing element 8 is supported by the end of the supporting body 6 facing the inlet of the gas turbine 1.
  • the sealing element 8 separates the lubrication zone of the bearing 7 from the zone of the rotor section 2 in which a cooling fluid circulates.
  • the sealing of the sealing element 8 is fundamental because the leakage of oil from the lubrication zone to the rotator section 2 could cause fires and severe damage to the gas turbine 1.
  • the sealing element 8 comprises a gasket 20 and a slide 21.
  • Both the gasket 20 and the slide 21, are arranged along the inner surface of the sealing element 8.
  • the slide 21 and the gasket 20 are provided in sequence along axis B so that in use the slide 21 is in contact with the lubrication oil of the bearing 7 and the seal 20 is in contact with the cooling fluid which circulates in the rotor section 2.
  • the gasket 20 is preferably metallic and comprises a plurality of metallic foils 22, which are arranged so as to form an array of rings substantially equidistant adapted to prevent the passage of lubrication oil and cooling fluid.
  • the metallic foils 22 must be made so as to leave a thin gap between the metallic foils 22 and the surface of the shaft 5a (in particular the surface of the respective plate of the shaft 5a), which will be occupied during use by a thin oil film which contributes to the correct sealing action of gasket 20.
  • Air conveyed by means of specific channels, circulates between each metallic foil 22, and contributes to cool the foils and creates a pressure on the foils which contrasts the pressure generated by the cooling fluid, so as to prevent the fluid from flowing into the lubrication zone of the rotor and, vice versa, the oil from leaking into the cooling fluid passage zone.
  • gasket 20 comprises a sealing ring, e.g. of the type commonly called “Corteco”, which comprises a spiral metallic ring, coated with a rubber ring which ensures the seal for direct contact with shaft 5a.
  • a sealing ring e.g. of the type commonly called “Corteco”
  • Corteco comprises a spiral metallic ring, coated with a rubber ring which ensures the seal for direct contact with shaft 5a.
  • the slide 21 is substantially a ring fixed to the inner surface of the sealing element 8 and has a contact face 24 made of low friction coefficient material. Preferably, the contact face 24 is coated with white metal.
  • the slide 21 has a diameter such as to leave a thin gap between the slide 21 and the surface of the shaft 5a (in particular the surface of the respective disc 5b of the shaft 5a). Such gap will be occupied during use by a thin film of oil which contributes to the correct sealing action of slide 21.
  • the slide 21 has a coupling edge 25, having a so-called “dovetail” shape, which engages the respective slide 26 made along the inner surface of the sealing element 8.
  • slide 21 is lubricated with the pressurized oil of the oscillating slides 18 of bearing 7.
  • the particular configuration of the sealing element 8 and of the supporting structure 6 allow the bearing assembly 4 to follow the position oscillations of the shaft 5a, particularly evident during the transient steps in which there is a variation of the rotation speed of shaft 5a. In this manner, stressing of the sealing element 8 is avoided, avoiding early deterioration of the sealing element 8 itself.
  • the particular configuration of the sealing element 8 and of the supporting structure 6 allows to avoid the long, demanding step of fixing of the supporting structure to the rotor section 2.
  • the supporting structure 6 must not be rigidly fixed to the stator section 3 by means of the traditional holes and alignment pins. This implies a considerable reduction of assembly and/or overall times and costs of the bearing assembly 4.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Support Of The Bearing (AREA)
EP11155903A 2010-02-24 2011-02-24 Lagerungsvorrichtung für die Welle einer Gasturbine Withdrawn EP2360351A1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
ITMI20100293 2010-02-24

Publications (1)

Publication Number Publication Date
EP2360351A1 true EP2360351A1 (de) 2011-08-24

Family

ID=42790662

Family Applications (1)

Application Number Title Priority Date Filing Date
EP11155903A Withdrawn EP2360351A1 (de) 2010-02-24 2011-02-24 Lagerungsvorrichtung für die Welle einer Gasturbine

Country Status (1)

Country Link
EP (1) EP2360351A1 (de)

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1374520A (en) * 1921-04-12 stanley smith cook
US1562019A (en) * 1922-09-05 1925-11-17 Gen Electric Shaft packing for elastic-fluid turbines and the like
US2591399A (en) * 1947-06-11 1952-04-01 Gen Electric Power plant frame structure having air-cooling means for turbine rotors and exhaust frame struts
GB1309495A (en) * 1970-05-25 1973-03-14 Owens Illinois Inc Fluid bearing structure
US4302062A (en) * 1979-09-20 1981-11-24 United Technologies Corporation Turbine blade support
US20060239816A1 (en) * 2005-04-21 2006-10-26 Pratt & Whitney Canada Integrated labyrinth and carbon seal
WO2009083789A1 (en) * 2007-12-28 2009-07-09 Ansaldo Energia S.P.A. Bearing assembly for a gas turbine

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1374520A (en) * 1921-04-12 stanley smith cook
US1562019A (en) * 1922-09-05 1925-11-17 Gen Electric Shaft packing for elastic-fluid turbines and the like
US2591399A (en) * 1947-06-11 1952-04-01 Gen Electric Power plant frame structure having air-cooling means for turbine rotors and exhaust frame struts
GB1309495A (en) * 1970-05-25 1973-03-14 Owens Illinois Inc Fluid bearing structure
US4302062A (en) * 1979-09-20 1981-11-24 United Technologies Corporation Turbine blade support
US20060239816A1 (en) * 2005-04-21 2006-10-26 Pratt & Whitney Canada Integrated labyrinth and carbon seal
WO2009083789A1 (en) * 2007-12-28 2009-07-09 Ansaldo Energia S.P.A. Bearing assembly for a gas turbine

Similar Documents

Publication Publication Date Title
US10436070B2 (en) Blade outer air seal having angled retention hook
RU2687474C2 (ru) Компрессор газотурбинного двигателя, содержащий лопатки с изменяемым углом установки
US20120211944A1 (en) Self-adjusting seal for rotating turbomachinery
JP5398651B2 (ja) 軸シール機構、及びこれを備えた回転機械
US20140363279A1 (en) Non-integral segmented angel-wing seal
US20140044526A1 (en) Stationary blade ring, assembly method and turbomachine
US8932001B2 (en) Systems, methods, and apparatus for a labyrinth seal
CN105026691A (zh) 燃气涡轮机转子叶片和燃气涡轮机转子
US20160010751A1 (en) Shaft seal device and rotary machine
US20160108737A1 (en) Blade system, and corresponding method of manufacturing a blade system
CA2793080C (en) Brush ring seal
EP3287619A1 (de) Variabler düsenmechanismus und turbolader mit variabler geometrie
RU2558486C2 (ru) Способ и направляющая для снятия внутреннего корпуса с турбомашины
JP2011252496A (ja) ターボ機械圧縮機用のパッチリングセグメント
US20110285090A1 (en) Seal assembly including plateau and concave portion in mating surface for seal tooth in turbine
JP2013181577A (ja) シール装置、及びこれを備えている回転機械
US9103224B2 (en) Compliant plate seal for use with rotating machines and methods of assembling a rotating machine
US10494944B2 (en) Seal on the inner ring of a guide vane
CN104246146B (zh) 用于涡轮机械同轴的轴之间密封的设备
RU2425270C1 (ru) Радиально-торцевое контактное уплотнение опоры турбомашины
EP2360351A1 (de) Lagerungsvorrichtung für die Welle einer Gasturbine
JP5802741B2 (ja) 回転陽極ｘ線管及び検査装置
CN204716310U (zh) 一种燃气轮机气封结构
JP4387697B2 (ja) 蒸気タービンシール装置およびそれを備えた蒸気タービン
CN101413425A (zh) 涡轮增压器用中间体总成

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

17P Request for examination filed

Effective date: 20120224

RIC1 Information provided on ipc code assigned before grant

Ipc: F01D 25/16 20060101ALI20120420BHEP

Ipc: F01D 11/02 20060101ALI20120420BHEP

Ipc: F01D 11/00 20060101AFI20120420BHEP

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN

18D Application deemed to be withdrawn

Effective date: 20121012