EP1224381B1 - Einrichtung zur kompensierung des axialschubs bei turbomaschinen - Google Patents

Einrichtung zur kompensierung des axialschubs bei turbomaschinen Download PDF

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Publication number
EP1224381B1
EP1224381B1 EP00975947A EP00975947A EP1224381B1 EP 1224381 B1 EP1224381 B1 EP 1224381B1 EP 00975947 A EP00975947 A EP 00975947A EP 00975947 A EP00975947 A EP 00975947A EP 1224381 B1 EP1224381 B1 EP 1224381B1
Authority
EP
European Patent Office
Prior art keywords
seal
axial
rotor
end seal
housing
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
EP00975947A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP1224381A1 (de
Inventor
Karl Urlichs
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.)
Alstom Power Turbinen GmbH
Original Assignee
Alstom Power Turbinen GmbH
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 Alstom Power Turbinen GmbH filed Critical Alstom Power Turbinen GmbH
Publication of EP1224381A1 publication Critical patent/EP1224381A1/de
Application granted granted Critical
Publication of EP1224381B1 publication Critical patent/EP1224381B1/de
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
    • F01D3/00—Machines or engines with axial-thrust balancing effected by working-fluid
    • F01D3/04—Machines or engines with axial-thrust balancing effected by working-fluid axial thrust being compensated by thrust-balancing dummy piston 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • 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
    • F05D2270/00—Control
    • F05D2270/30—Control parameters, e.g. input parameters
    • F05D2270/301—Pressure

Definitions

  • the invention relates to a device for compensating the Axial thrust in turbomachines according to the preamble of Claim 1.
  • From DE-GM 17 01 436 is an auxiliary device trained device for Axialkraftkompensation known which is available in addition to a thrust bearing.
  • the thrust bearing absorbs the axial forces.
  • the device is the partial compensation of the axial forces activated.
  • WO 99/30007 From WO 99/30007 is a turbine with a Balancing piston known in which a brush seal on Equalizing piston is provided.
  • the respective diameter of axial seal and Radial seal is dependent on the functional diameter the turbo machine selected.
  • the axial seal is preferably as a mechanical seal or designed as a brush seal.
  • the use of a Slip ring or brush seal results in a rigid seal assembly, the only too small displacements of the Turbine rotor leads.
  • the axial seal is another axial seal juxtaposed with a larger base gap width Is provided.
  • This secondary seal serves as a safety seal. It is only due to its larger base gap Use when the main seal fails.
  • the rotor be associated with a thrust bearing, due to its Gap width only with extreme opening of the seal chamber Use comes in normal operation and no axial forces transmits and causes no friction losses.
  • FIG. 1 shows the partial area of a turbomachine 1 with a rotor 2 and a housing 3. Between the housing 3 and the rotor 2 a plurality of guide wheels and running wheels, not shown in FIG. 1, are arranged in the area marked 4. The guide wheels connected to the housing 3 and the wheels connected to the rotor 2 are flowed through by a medium 5, which has a pre-pressure p 1 and is supplied via a connecting piece 5. After flowing through the wheels, the medium has a final pressure p 2 .
  • a rotating in a compensation chamber disc which forms a compensating piston 9 in conjunction with a radial seal 7 and a Axiadichtung 8.
  • the pressure after the balance piston 9 is ensured by a compensation line 10 in a space 11, which is acted upon by the final pressure p 2 .
  • the example formed as a brush seal axial seal 8 is disposed on a predetermined diameter d k and fixed to the housing 3.
  • gap width S referred to as the axial gap width
  • the gap width S being reduced by the amount of thrust movement in the event of a pushing movement of the running wheels and of the rotor 2 in the direction of the arrow F ax , since the compensating piston 9 also carries out the pushing movement.
  • the axial seal 8 is designed very "stiff", their tightness changes even with small changes in the gap width S to a considerable extent.
  • With reduced gap width S of the pressure in the compensation chamber 6 reaches almost the pressure level of the form p 1 .
  • a pressure which equals the final pressure p 2 arises due to the equalization line 10 in the compensation chamber 6.
  • the functional diameter of the turbomachinery d i and d m are matched with the arrangement diameter d k of the axial seal and not shown in FIG. 1 arrangement diameter d z of the radial seal 7 so that all boundary areas of the application detected become. Due to the absolutely self-regulating process, the displacement force of the running path is constantly compensated, so that the balance of power is always maintained even with fluctuating axial thrusts.
  • Figure 2 shows a partial section of the housing 3 with the nozzle 5 for the under a form p, fed medium.
  • the impeller in the region 4 with the mean diameter d m of its blading is flowed through by the medium, resulting in an axial thrust in the direction of arrow F ax .
  • the compensating piston 9 protrudes into the compensation chamber 6, wherein between its outer diameter d z and the housing 3, the radial seal 7 is provided.
  • the axial seal 8 is formed as an axially acting mechanical seal, which consists of undivided seals, the fluid-supported slide on each other.
  • a sliding ring 12 is the housing 3 and a counter ring 13 is associated with the balance piston 9 to form a gap width S.
  • the cut according to Figure 3 shows a radially inward between the balance piston 9 and the housing 3 arranged axial seal 8 with a gap width S.
  • axial seal 8a In order to increase the operational safety is positioned radially outward acting as a security seal further axial seal 8a n with S has a greater gap width than the axial seal 8. The axial seal 8a will therefore come only when failure of the axial seal 8 are used.
  • the pressure in the chamber 6a is measured and compared with the final pressure p 2 .
  • the axial seals 8 and 8a are arranged next to one another in the axial direction, with the axial seal 8a having its larger gap width S n only being used when the axial seal 8 should fail.
  • the pressure in the chamber 6a is measured and compared with the final pressure p 2 .
  • FIG. 5 A section of the illustration according to FIG. 1 is shown in FIG. 5 shown.
  • a thrust bearing 14 intended. Due to the distances 15 and 16 is the Thrust bearing including an injection lubrication so designed so that it is used only in the border area. On This way, the usual losses of this camp avoided.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Sealing Using Fluids, Sealing Without Contact, And Removal Of Oil (AREA)
  • Sealing Devices (AREA)
  • Paper (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP00975947A 1999-10-27 2000-10-27 Einrichtung zur kompensierung des axialschubs bei turbomaschinen Expired - Lifetime EP1224381B1 (de)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE19951570 1999-10-27
DE19951570A DE19951570A1 (de) 1999-10-27 1999-10-27 Einrichtung zur Kompensierung des Axialschubs bei Turbomaschinen
PCT/EP2000/010619 WO2001031169A1 (de) 1999-10-27 2000-10-27 Einrichtung zur kompensierung des axialschubs bei turbomaschinen

Publications (2)

Publication Number Publication Date
EP1224381A1 EP1224381A1 (de) 2002-07-24
EP1224381B1 true EP1224381B1 (de) 2005-02-02

Family

ID=7926934

Family Applications (1)

Application Number Title Priority Date Filing Date
EP00975947A Expired - Lifetime EP1224381B1 (de) 1999-10-27 2000-10-27 Einrichtung zur kompensierung des axialschubs bei turbomaschinen

Country Status (8)

Country Link
US (1) US6609882B2 (ja)
EP (1) EP1224381B1 (ja)
JP (1) JP4485729B2 (ja)
AT (1) ATE288536T1 (ja)
CZ (1) CZ297939B6 (ja)
DE (2) DE19951570A1 (ja)
ES (1) ES2235985T3 (ja)
WO (1) WO2001031169A1 (ja)

Families Citing this family (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE50206223D1 (de) * 2001-10-22 2006-05-18 Sulzer Pumpen Ag Wellenabdichtungsanordnung für eine Pumpe zur Förderung heisser Fluide
GB2411931A (en) * 2004-03-08 2005-09-14 Alstom Technology Ltd A leaf seal arrangement
US7195443B2 (en) * 2004-12-27 2007-03-27 General Electric Company Variable pressure-controlled cooling scheme and thrust control arrangements for a steam turbine
US7549835B2 (en) 2006-07-07 2009-06-23 Siemens Energy, Inc. Leakage flow control and seal wear minimization system for a turbine engine
DE102008022966B4 (de) * 2008-05-09 2014-12-24 Siemens Aktiengesellschaft Rotationsmaschine
US20090304493A1 (en) * 2008-06-09 2009-12-10 General Electric Company Axially oriented shingle face seal for turbine rotor and related method
EP2154332A1 (de) * 2008-08-14 2010-02-17 Siemens Aktiengesellschaft Verminderung der thermischen Belastung eines Aussengehäuses für eine Strömungsmaschine
US8061970B2 (en) * 2009-01-16 2011-11-22 Dresser-Rand Company Compact shaft support device for turbomachines
US8277177B2 (en) 2009-01-19 2012-10-02 Siemens Energy, Inc. Fluidic rim seal system for turbine engines
US20100196139A1 (en) * 2009-02-02 2010-08-05 Beeck Alexander R Leakage flow minimization system for a turbine engine
US8186933B2 (en) * 2009-03-24 2012-05-29 General Electric Company Systems, methods, and apparatus for passive purge flow control in a turbine
US9024493B2 (en) 2010-12-30 2015-05-05 Dresser-Rand Company Method for on-line detection of resistance-to-ground faults in active magnetic bearing systems
US8994237B2 (en) 2010-12-30 2015-03-31 Dresser-Rand Company Method for on-line detection of liquid and potential for the occurrence of resistance to ground faults in active magnetic bearing systems
US9551349B2 (en) 2011-04-08 2017-01-24 Dresser-Rand Company Circulating dielectric oil cooling system for canned bearings and canned electronics
WO2012166236A1 (en) 2011-05-27 2012-12-06 Dresser-Rand Company Segmented coast-down bearing for magnetic bearing systems
US8851756B2 (en) 2011-06-29 2014-10-07 Dresser-Rand Company Whirl inhibiting coast-down bearing for magnetic bearing systems
DE102017212821A1 (de) * 2017-07-26 2019-01-31 Robert Bosch Gmbh Turbomaschine, insbesondere für ein Brennstoffzellensystem
CN114856720B (zh) * 2022-04-20 2023-04-25 浙大宁波理工学院 一种用于超高速涡轮转子的密封装置

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE289941C (ja) *
US1151965A (en) * 1913-08-12 1915-08-31 Laval Steam Turbine Co Balancing of centrifugal pumps.
BE380057A (ja) * 1930-05-27
US2005429A (en) * 1932-03-21 1935-06-18 Foster Wheeler Corp Centrifugal pump and the like
DE1701347U (de) * 1954-09-08 1955-06-30 Karl Dr Roder Drucklager in turbomaschinen.
DE1701436U (de) * 1955-04-20 1955-06-30 Degussa Apparategehaeuse und teile von solchen aus nichtmetallischem material mit lack- und metallueberzuegen.
DE3424138A1 (de) * 1984-06-30 1986-01-09 BBC Aktiengesellschaft Brown, Boveri & Cie., Baden, Aargau Luftspeichergasturbine
US5104284A (en) * 1990-12-17 1992-04-14 Dresser-Rand Company Thrust compensating apparatus
DE4422594A1 (de) * 1994-06-28 1996-01-04 Abb Patent Gmbh Kondensationsturbine mit mindestens zwei Dichtungen zur Abdichtung des Turbinengehäuses
US6079945A (en) * 1997-11-10 2000-06-27 Geneal Electric Company Brush seal for high-pressure rotor applications
US6067791A (en) * 1997-12-11 2000-05-30 Pratt & Whitney Canada Inc. Turbine engine with a thermal valve

Also Published As

Publication number Publication date
ATE288536T1 (de) 2005-02-15
US20020197150A1 (en) 2002-12-26
EP1224381A1 (de) 2002-07-24
CZ297939B6 (cs) 2007-05-02
DE50009437D1 (de) 2005-03-10
JP2003513188A (ja) 2003-04-08
WO2001031169A1 (de) 2001-05-03
JP4485729B2 (ja) 2010-06-23
ES2235985T3 (es) 2005-07-16
US6609882B2 (en) 2003-08-26
DE19951570A1 (de) 2001-05-03
CZ20021454A3 (cs) 2002-10-16

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