EP0891471B1 - Verfahren und vorrichtung zum schubausgleich bei einer turbomaschine - Google Patents

Verfahren und vorrichtung zum schubausgleich bei einer turbomaschine Download PDF

Info

Publication number
EP0891471B1
EP0891471B1 EP97918065A EP97918065A EP0891471B1 EP 0891471 B1 EP0891471 B1 EP 0891471B1 EP 97918065 A EP97918065 A EP 97918065A EP 97918065 A EP97918065 A EP 97918065A EP 0891471 B1 EP0891471 B1 EP 0891471B1
Authority
EP
European Patent Office
Prior art keywords
pressure
inner casing
turbomachine
thrust compensation
axial
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
EP97918065A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP0891471A1 (de
Inventor
Axel Remberg
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
Siemens Corp
Original Assignee
Siemens AG
Siemens Corp
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, Siemens Corp filed Critical Siemens AG
Publication of EP0891471A1 publication Critical patent/EP0891471A1/de
Application granted granted Critical
Publication of EP0891471B1 publication Critical patent/EP0891471B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/26—Double casings; Measures against temperature strain in casings
    • 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
    • F01D25/26—Double casings; Measures against temperature strain in casings
    • F01D25/265—Vertically split casings; Clamping arrangements therefor
    • 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

Definitions

  • the present invention relates to a method and a Device in a turbomachine with an outer and a Inner housing or guide vane carrier for thrust compensation.
  • the field of application of the invention is included Turbomachines in pot design, the pressure of a axial fluid flowing through the turbomachine in the longitudinal direction of the shaft at least on the inner housing caused.
  • DE 22 18 500 is a multi-shell housing a steam turbine for high steam pressures and temperatures described.
  • live steam comes at high pressure into the inner case. After an expansion of about 20% of the The entire gradient of the turbine part is the steam through drilling led into the outer housing and so presses in the area further expansion course the inner housing in the area of the joints.
  • guide vane carrier is chosen. in this connection the full live steam pressure is in the space between inside and Outer housing and thus presses the two support halves together.
  • the term further includes the term "Inner housing" is always the constructive solution with a guide vane carrier.
  • DE 22 18 500 discloses a multi-shell Steam turbine housing for high steam pressures and temperatures.
  • An inner shell is made using a support ring clamped against the outer housing and thus axially fixed.
  • the US 3,754,833 in turn or its priority document, the DE 20 54 465 describes a device for radial-centric heat-moving storage and centering of shaft seal housings on the outer casing of turbomachinery.
  • the turbine shown there has a pot housing an axis-normal parting line.
  • a carrying the guide vanes Inner housing is in the pot housing on a Lagerund Centering point used. This centering point will formed by a Uhde board cutter closure.
  • Bypass channels in the inner housing are used for axial thrust compensation.
  • the object of the present invention is therefore to create of a method for thrust compensation in a turbomachine and a corresponding design of the same.
  • the invention is intended to produce axial forces in the longitudinal direction balance the wave.
  • the invention provides that at least a first surface of the Exterior of part of the inner housing for axial thrust compensation divided into two sections for axial thrust compensation is applied, each with different pressure a distinction between the two pressures caused by at least one means, in particular a seal becomes.
  • the exterior of a part of the inner housing is preferred pressurized to compensate for axial thrust, which is at least as large as the outlet pressure of the Is fluid, and preferably about as large as the inlet pressure.
  • the Pressure for axial thrust compensation of the axial force of the outlet pressure towards the inner housing Because of the overlay both pressures result in a reduced resulting Pressure that also causes less thrust.
  • This axial thrust compensation is particularly on the inner housing the turbomachine feasible. This ensures that the previous high construction costs for fixing the inner housing can be reduced. The occurring on the fixing elements Surface pressures are therefore lower and therefore lead also to smaller deformations.
  • the invention is the pressure on the outside Part of the inner case according to the operating conditions such as full or partial load. By suitable The pressure is then controlled on the inner housing occurring axial thrust adjustable.
  • the suitable means preferably a seal.
  • the axial thrust compensation of the inner housing is therefore not can only be influenced by the pressure, but also by the Pressure available effective area to form a Axial force.
  • This acting surface becomes the first surface now divided into two areas by the mean.
  • the active surface comprises at least one Part of the outer face of the inner case.
  • the machine has the possibility of finding a suitable one Dimension of the outer part of the inner housing for Axial thrust compensation to make this thrust so small to keep as possible.
  • the axial thrust is also a part of a turbine Variation of the areas, determined by means of the diameter one or two I-ring seals, also adjustable.
  • the seal itself is thus pressurized and particularly burdened. Because of the seal it is on both Partial pressure acting between the inside and External housing attachable.
  • Figure 1 shows an embodiment of an inventive Turbo machine 1, a high-pressure turbine 1 in pot design, which has an inner housing 2 and an outer housing 3.
  • the fluid 4 flowing through the turbomachine 1 also joins the inlet pressure P1 and leaves the high-pressure turbine 1 again with the outlet pressure P2.
  • the pressure difference between the inlet and outlet pressure leads to an axial thrust not only on the inner housing 2 but also on the shaft 5.
  • the inner housing 2 has one on its outside Surface A1, which acts on the inlet pressure P1 becomes.
  • a pressure on the surface A1 is preferably at least this large as the outlet pressure P2 of the fluid 4 from the turbomachine 1.
  • the pressure on the area A1 can also as large as the inlet pressure of the fluid and / or a pressure be inside the inner housing 2.
  • the Area A1 part of the end face of the inner housing 2.
  • the Axial thrust arising on this surface A1 overlaps the of the surface A2 'created axial force on the inner housing 2, whereby axial thrust compensation takes place on this.
  • the fixation 6 of the inner housing 2 relative to the outer housing 3 is lower surface pressures due to this axial thrust compensation subjected.
  • This allows a variety of construction options to initiate an axial thrust in the outer housing 3, for. B. can in the previous state of Support rings used in technology are eliminated.
  • the overall structure Such a turbomachine according to the invention can be thus simplify due to the improved axial thrust compensation.
  • the axial pressure transmitting Area A1 of the outer part of the inner casing 2 by means arranged around the shaft 5 7 limited.
  • This means 7 advantageously a seal, limits the attacking pressure P1 to the axial pressure transmitting one Area A1, so that by using means 7 a precisely defined axial thrust compensation can take place.
  • the use of such a means 7 Possibility to add another area A3 to the outer part of the To apply another pressure P3 to the inner housing 2.
  • the pressure P3 in connection with the area A3 then generates also a contribution to axial thrust compensation.
  • the areas A1 and A3 together therefore form a for the purposes of the invention first surface of the outer part of the inner housing 2.
  • the Areas A1 and A3 individually are the partial areas.
  • the pressure P3 which is advantageous compared to the pressure P1 lower, serves as a barrier pressure. Pressure and flow losses over the or the seals as a means 7 can can be reduced by means of this advantageous pressure rating. This makes the seal, especially an I-ring seal not only pressurized, but also with the Can withstand pressure. By using several means 7 can For a better pressure rating also other, separate from each other Surfaces for axial thrust compensation are created, like this by the dotted line 7 with the area A3 ' and the pressure P3 'is indicated. Because of the building geometry the turbomachine 1 is advantageously the seal 7 between the inner part of the outer housing 3 and the outer Part of the inner housing 2 attached, in particular so that it direct contact with the inner housing 2 and the outer housing 3 Has.
  • the invention provides that an axial thrust compensation not only on the inner housing 2 but also on the Wave 5 takes place.
  • the turbomachine is designed so that an axial pressure transmitting surface A2 '' with the outlet pressure P2 is applied. So, because of the Pressure difference between the inlet pressure P1 and the outlet pressure P2 above the blades, axial thrust occurring at the Wave 5 are at least partially compensated.
  • Figure 2 shows the arrangement in a schematic representation a high pressure part HD, a medium pressure part MD and of a low pressure part ND of a turbine on a shaft.
  • This illustration shows that the forces from the pressure P1 on surface A1 and from print P3 on surface A3 act in the negative X direction. The force from the pressure P2 however, these forces have a positive effect on the area A2 '' X direction opposite.
  • the invention is therefore not only one Part turbine, but rather on a strand of turbo machines connected in series for axial thrust compensation applicable.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Basic Packing Technique (AREA)
EP97918065A 1996-04-11 1997-04-02 Verfahren und vorrichtung zum schubausgleich bei einer turbomaschine Expired - Lifetime EP0891471B1 (de)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE19614335 1996-04-11
DE19614335 1996-04-11
PCT/DE1997/000674 WO1997038209A1 (de) 1996-04-11 1997-04-02 Verfahren und vorrichtung zum schubausgleich bei einer turbomaschine

Publications (2)

Publication Number Publication Date
EP0891471A1 EP0891471A1 (de) 1999-01-20
EP0891471B1 true EP0891471B1 (de) 2002-06-26

Family

ID=7791006

Family Applications (1)

Application Number Title Priority Date Filing Date
EP97918065A Expired - Lifetime EP0891471B1 (de) 1996-04-11 1997-04-02 Verfahren und vorrichtung zum schubausgleich bei einer turbomaschine

Country Status (11)

Country Link
US (1) US6213710B1 (pl)
EP (1) EP0891471B1 (pl)
JP (1) JP2000508040A (pl)
KR (1) KR20000005303A (pl)
CN (1) CN1081724C (pl)
AT (1) ATE219816T1 (pl)
CZ (1) CZ326498A3 (pl)
DE (1) DE59707599D1 (pl)
PL (1) PL183594B1 (pl)
RU (1) RU2175721C2 (pl)
WO (1) WO1997038209A1 (pl)

Families Citing this family (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR20010072537A (ko) * 1997-11-03 2001-07-31 칼 하인쯔 호르닝어 터빈 하우징 및 그 제조 방법
JP3986873B2 (ja) * 2001-05-08 2007-10-03 花王株式会社 液体洗浄剤組成物
DE60121968T2 (de) * 2001-11-22 2006-12-07 Siemens Ag Verfahren zum Herstellen von Dampfturbinen
JP2006016976A (ja) * 2004-06-30 2006-01-19 Toshiba Corp タービンノズル支持装置および蒸気タービン
US7195443B2 (en) * 2004-12-27 2007-03-27 General Electric Company Variable pressure-controlled cooling scheme and thrust control arrangements for a steam turbine
US7520721B2 (en) * 2006-09-19 2009-04-21 General Electric Company System and method for aligning and sealing a turbine shell assembly
US8256575B2 (en) * 2007-08-22 2012-09-04 General Electric Company Methods and systems for sealing rotating machines
WO2009123301A2 (en) * 2008-03-31 2009-10-08 Mitsubishi Heavy Industries, Ltd. Rotary machine
DE102008022966B4 (de) * 2008-05-09 2014-12-24 Siemens Aktiengesellschaft Rotationsmaschine
EP2192266A1 (en) * 2008-11-26 2010-06-02 Siemens Aktiengesellschaft Rotor device for a steam turbine and steam turbine
JP2010174795A (ja) * 2009-01-30 2010-08-12 Mitsubishi Heavy Ind Ltd タービン
CH701914A1 (de) * 2009-09-30 2011-03-31 Alstom Technology Ltd Dampfturbine mit Entlastungsnut am Rotor im Bereich des Schubausgleichskolbens.
EP2333253A1 (de) * 2009-12-08 2011-06-15 Siemens Aktiengesellschaft Innengehäuse für eine Strömungsmaschine
KR20250154299A (ko) 2025-10-01 2025-10-28 (주)태일기공 유가금속 정광 처리시 발생하는 미세먼지와 폐수 재활용 처리 장치 및 그 방법

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE281253C (pl) *
FR1094273A (fr) * 1953-08-31 1955-05-16 Siemens Ag Turbine à double enveloppe fonctionnant à forte pression d'échappement
DE1152703B (de) * 1959-12-14 1963-08-14 Licentia Gmbh Vielstufige Gleichdruckturbine
CH499012A (de) * 1968-12-03 1970-11-15 Siemens Ag Anordnung zur axial festen und radial beweglichen Lagerung von Turbinengehäuseteilen
JPS5227282B2 (pl) 1970-11-05 1977-07-19
DE2218500B2 (de) * 1972-04-17 1974-01-31 Kraftwerk Union AG, 4330 Mülheim Mehrschaliges gehaeuse einer dampfturbine fuer hohe dampfdruecke und dampftemperaturen
JPS59213907A (ja) * 1983-05-19 1984-12-03 Fuji Electric Co Ltd つぼ型タ−ビン
CA1326476C (en) * 1988-09-30 1994-01-25 Vaclav Kulle Gas compressor having dry gas seals for balancing end thrust

Also Published As

Publication number Publication date
PL329236A1 (en) 1999-03-15
CZ326498A3 (cs) 1999-02-17
DE59707599D1 (de) 2002-08-01
EP0891471A1 (de) 1999-01-20
KR20000005303A (ko) 2000-01-25
WO1997038209A1 (de) 1997-10-16
US6213710B1 (en) 2001-04-10
ATE219816T1 (de) 2002-07-15
RU2175721C2 (ru) 2001-11-10
JP2000508040A (ja) 2000-06-27
CN1215449A (zh) 1999-04-28
PL183594B1 (pl) 2002-06-28
CN1081724C (zh) 2002-03-27

Similar Documents

Publication Publication Date Title
EP2862262B1 (de) Kühlmantel mit einem dichtmittel
DE102009005013B4 (de) Verbindungsanordnung eines Turbinengehäuses mit einem Lagergehäuse und Abgasturbolader
EP3548705B1 (de) Turbolader
EP2466074A1 (de) Gasturbinentriebwerk mit Kolbenringdichtung
DE2119113A1 (de) Selbsteinstellende Dichtungsanordnung
WO1997038209A1 (de) Verfahren und vorrichtung zum schubausgleich bei einer turbomaschine
DE102012008723A1 (de) Leitrad für Turbomaschinen und Herstellungsverfahren
EP2271827A1 (de) Turbomaschine mit schubausgleichskolben
DE102009029587A1 (de) Rotor einer Turbomaschine
EP0953099B1 (de) Dampfturbine
EP1676980A1 (de) Turbolader mit variabler Turbinengeometrie und Herstellungsverfahren
DE68901768T2 (de) Kompressorgehaeuse mit regelbarem innendurchmesser fuer eine turbomaschine.
EP3571380B1 (de) Turbinengehäuse und verfahren zur montage einer turbine mit einem turbinengehäuses
CH698121B1 (de) Gruppierte Reaktionsdüsen-Deckbänder mit integrierten Dichtungen.
DE2348501A1 (de) Zuendeinrichtung fuer gasturbinentriebwerk
DE1286810B (de) Laufschaufelradialspalt-Abdeckring einer Axialturbomaschine, insbesondere -gasturbine
DE102010005153A1 (de) Gehäusesystem für eine Axialströmungsmaschine
DE102010041210A1 (de) Gehäuse
EP2665896B1 (de) Zwischengehäuse einer Gasturbine mit einer aussen liegenden Begrenzungswand welche stromaufwärts einer Stützrippe eine in Umfangrichtung verändernde Kontur aufweist zur Verringerung der Sekundärströmungsverluste
EP3670845A1 (de) Statische dichtungsanordnung und turbomaschine
DE10115947C2 (de) Verfahren zur Relativpositionierung von aufeinander folgenden Statoren oder Rotoren einer transsonischen Hochdruckturbine
DE3320190A1 (de) Lastverteilervorrichtung, insbesondere fuer die turbine eines gasturbinentriebwerks
EP2161415B1 (de) Vorrichtung und Verfahren zur Reduzierung des Drucks auf eine Trennfuge zwischen wenigstens zwei Begrenzungsteilen
DE102019109056A1 (de) Verbrennungsmotor mit turbolader
DE3737344A1 (de) Wellendichtung fuer gasgefuellte elektrische maschinen

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

17P Request for examination filed

Effective date: 19981005

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AT CH DE ES FR GB IT LI NL SE

GRAG Despatch of communication of intention to grant

Free format text: ORIGINAL CODE: EPIDOS AGRA

GRAG Despatch of communication of intention to grant

Free format text: ORIGINAL CODE: EPIDOS AGRA

GRAH Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOS IGRA

17Q First examination report despatched

Effective date: 20011010

GRAH Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOS IGRA

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AT CH DE ES FR GB IT LI NL SE

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: NL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20020626

REF Corresponds to:

Ref document number: 219816

Country of ref document: AT

Date of ref document: 20020715

Kind code of ref document: T

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

REF Corresponds to:

Ref document number: 59707599

Country of ref document: DE

Date of ref document: 20020801

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20020926

GBT Gb: translation of ep patent filed (gb section 77(6)(a)/1977)

Effective date: 20020906

NLV1 Nl: lapsed or annulled due to failure to fulfill the requirements of art. 29p and 29m of the patents act
ET Fr: translation filed
PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: ES

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20021220

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: AT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20030402

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20030430

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20030430

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

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

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed

Effective date: 20030327

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 20

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20160620

Year of fee payment: 20

Ref country code: GB

Payment date: 20160411

Year of fee payment: 20

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: IT

Payment date: 20160428

Year of fee payment: 20

Ref country code: FR

Payment date: 20160429

Year of fee payment: 20

REG Reference to a national code

Ref country code: DE

Ref legal event code: R071

Ref document number: 59707599

Country of ref document: DE

REG Reference to a national code

Ref country code: GB

Ref legal event code: PE20

Expiry date: 20170401

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Free format text: LAPSE BECAUSE OF EXPIRATION OF PROTECTION

Effective date: 20170401