DE19719770A1 - Turbine machine - Google Patents

Turbine machine

Info

Publication number
DE19719770A1
DE19719770A1 DE1997119770 DE19719770A DE19719770A1 DE 19719770 A1 DE19719770 A1 DE 19719770A1 DE 1997119770 DE1997119770 DE 1997119770 DE 19719770 A DE19719770 A DE 19719770A DE 19719770 A1 DE19719770 A1 DE 19719770A1
Authority
DE
Germany
Prior art keywords
housing
support structure
annular support
turbomachine
turbo machine
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Withdrawn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
DE1997119770
Other languages
German (de)
Inventor
Urs Benz
Hans-Juergen Dr Kiesow
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.)
General Electric Switzerland GmbH
Original Assignee
Asea Brown Boveri AG Switzerland
Asea Brown Boveri AB
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 Asea Brown Boveri AG Switzerland, Asea Brown Boveri AB filed Critical Asea Brown Boveri AG Switzerland
Priority to DE1997119770 priority Critical patent/DE19719770A1/en
Priority to GB9808224A priority patent/GB2328477A/en
Priority to CN 98107968 priority patent/CN1199132A/en
Priority to JP12590898A priority patent/JPH10317913A/en
Publication of DE19719770A1 publication Critical patent/DE19719770A1/en
Withdrawn legal-status Critical Current

Links

Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02CGAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/20Mounting or supporting of plant; Accommodating heat expansion or creep
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/28Supporting or mounting arrangements, e.g. for turbine casing
    • F01D25/285Temporary support structures, e.g. for testing, assembling, installing, repairing; Assembly methods using such structures
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05DINDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00Manufacture
    • F05D2230/70Disassembly methods

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Hydraulic Turbines (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

The turbine machine (1) has a casing (2) containing the rotor, combustion chambers, cooling system etc. There is an annular bearing structure (3) in the casing, which can rotate and can be locked in at least one position. All the components (5) which have to be checked or changed periodically are mounted on this bearing structure. The bearing structure may be connected to a device which can turn it into different working positions as required. The device is between the casing and the bearing structure, or between the bearing structure and the rotor.

Description

Technisches GebietTechnical field

Die Erfindung betrifft eine Turbomaschine nach dem Oberbegriff des Patent­ anspruchs 1.The invention relates to a turbomachine according to the preamble of the patent claim 1.

Stand der TechnikState of the art

Bei Turbomaschinen müssen regelmäßig im Zusammenhang mit Wartungsar­ beiten Baugruppen kontrolliert oder ausgebaut und ersetzt werden. Dazu ist es erforderlich, daß im allgemeinen das Oberteil, die obere Halbschale des Gehäuses der Turbomaschine abgenommen wird, um Zugang zu diesen Bau­ gruppen zu erhalten. Solche Teildemontagen sind sehr aufwendig und zeit­ raubend, daher teuer. Insbesondere um vielfach nur festzustellen, daß die über­ prüften Baugruppen weiterhin funktionstüchtig sind. Außerdem erfordert eine solche Teildemontage unverhältnismäßig viel Montagezeit gegenüber der eigentlichen Prüfzeit.For turbomachinery, they must be regularly related to maintenance be checked or removed and replaced. It is for that required that in general the upper part, the upper half-shell of the Housing of the turbomachine is removed to give access to this construction groups. Such partial disassembly is very complex and time consuming, therefore expensive. In particular, in order to determine that the over tested modules are still functional. It also requires one such partial disassembly disproportionate time compared to the actual test time.

Darstellung der ErfindungPresentation of the invention

Die Erfindung versucht, diese Nachteile zu vermeiden. Es liegt ihr die Aufgabe zugrunde, eine Turbomaschine anzugeben, bei welcher zur Überprüfung oder zum Austausch von Baugruppen Teildemontagen im bisherigen Umfang nicht erforderlich sind. The invention tries to avoid these disadvantages. It is her job based on specifying a turbomachine for which to check or not for the replacement of assemblies required are.  

Die Lösung dieser Aufgabe wird mit den Merkmalen des Kennzeichens von Patentanspruch 1 umschrieben. Vorteilhafte Ausführungsformen einer Tur­ bomaschine sind durch die Merkmale der abhängigen Ansprüche angegeben.The solution to this problem is with the characteristics of the indicator of Claim 1 circumscribed. Advantageous embodiments of a door bomaschine are indicated by the features of the dependent claims.

Kurze Beschreibung der ZeichnungBrief description of the drawing

Weitere Merkmale und Vorteile ergeben sich aus der Beschreibung einer beispielsweisen Ausführungsform anhand der Zeichnung. In dieser zeigt:Further features and advantages result from the description of a exemplary embodiment with reference to the drawing. In this shows:

Fig. 1 schematisch einen Teil des Gehäuses einer Turbomaschine, teilweise aufgeschnitten, Fig. 1 shows diagrammatically, partially cut away part of the casing of a turbomachine,

Fig. 2 schematisch einen teilweisen Schnitt (AA) durch die Turbomaschine senkrecht zu ihrer Achse. Fig. 2 shows schematically a partial section (AA) through the turbo machine perpendicular to its axis.

Es sind nur die für das Verständnis der Erfindung wesentlichen Elemente gezeigt; insbesondere ist nicht der an sich bekannte und unveränderte Teil der Turbomaschine oder andere ihrer Details etc. dargestellt.They are only the elements essential for understanding the invention shown; in particular, the part of the Turbomachine or other of its details etc. shown.

Weg zur Ausführung der ErfindungWay of carrying out the invention

Bei einer Turbomaschine 1 mit einem Gehäuse 2, in welchem ein Rotor 4 gelagert ist und das die Peripheriebaugruppen, wie Brennkammern, Kühlsys­ teme, etc. enthält, ist eine ringförmige Tragstruktur 3 im Gehäuse 2 vorgesehen. Diese ringförmige Tragstruktur 3 ist im Gehäuse drehbar gelagert und in wenig­ stens einer Position verriegelbar. Auf ihr sind alle periodisch zu überprüfenden oder auszuwechselnden Baugruppen 5 montiert. Um die ringförmige Tragstruktur 3 bei Bedarf anläßlich einer Revision der Turbomaschine 1 in verschiedene Montage oder Revisionspositionen drehen zu können, ist sie mit einer Einrich­ tung verbunden, welche einerseits die ringförmige Tragstruktur 3 in der Betriebs­ stellung verriegelt und andererseits sie in die erforderlichen Montage oder Revisionspositionen bewegt. Diese Einrichtung zum Drehen der ringförmigen Tragstruktur 3 ist zwischen dem Gehäuse 2 und der ringförmigen Tragstruktur 3 oder zwischen dieser und dem Rotor 4 angeordnet. Das Gehäuse 2 der Turbo­ maschine 1 weist wenigstens eine verschließbare Montageöffnung 6 auf, welche eine solche Größe und Form hat, daß die zu kontrollierenden oder zu ersetzenden Baugruppen 5 der Turbomaschine 1 leicht zugänglich sind bzw. ausgebaut und entfernt werden können. Insbesondere sind bei mehreren Montageöffnungen 6 diese im wesentlichen in zwei achsnormalen Ebenen angeordnet, welche den im Innern des Gehäuses 2 vorhandenen Baugruppen 5 entsprechen. Damit ist gewährleistet, daß die Baugruppen 5 der Turbomaschine zugänglich sind, wodurch sich die Stillstandszeit wesentlich verringert. Zudem muß bei einer solcherweise ausgebildeten Turbomaschine nicht mehr das Gehäuse teilweise demontiert werden, um zu den zu ersetzenden oder zu kontrollierenden Baugruppen 5 Zugang zu erhalten. Dies bewirkt wesentliche Einsparungen bei der Revision.In a turbomachine 1 with a housing 2 , in which a rotor 4 is mounted and which contains the peripheral assemblies, such as combustion chambers, cooling systems, etc., an annular support structure 3 is provided in the housing 2 . This annular support structure 3 is rotatably mounted in the housing and can be locked in at least one position. All modules 5 to be checked or replaced periodically are mounted on it. In order to be able to rotate the ring-shaped support structure 3 when required during a revision of the turbomachine 1 into different assembly or revision positions, it is connected to a device which, on the one hand, locks the ring-shaped support structure 3 in the operating position and, on the other hand, it into the required assembly or revision positions emotional. This device for rotating the annular support structure 3 is arranged between the housing 2 and the annular support structure 3 or between the latter and the rotor 4 . The housing 2 of the turbo machine 1 has at least one lockable mounting opening 6 , which has such a size and shape that the assemblies 5 to be checked or replaced of the turbomachine 1 are easily accessible or can be removed and removed. In particular, in the case of a plurality of assembly openings 6, these are arranged essentially in two axially normal planes, which correspond to the assemblies 5 present in the interior of the housing 2 . This ensures that the assemblies 5 of the turbomachine are accessible, which significantly reduces the downtime. In addition, in the case of a turbomachine designed in this way, the housing no longer has to be partially dismantled in order to gain access to the assemblies 5 to be replaced or checked. This leads to significant savings in the revision.

BezugszeichenlisteReference list

11

Turbomaschine
Turbo machine

22nd

Gehäuse
casing

33rd

ringförmige Tragstruktur
annular support structure

44th

Rotor
rotor

55

Baugruppen (für Revision)
Assemblies (for revision)

66

Montageöffnung
Assembly opening

Claims (5)

1. Turbomaschine mit einem Gehäuse, in welchem ein Rotor gelagert ist und das die Baugruppen, wie Brennkammern, Kühlsysteme, etc. enthält, dadurch gekennzeichnet, daß eine ringförmige Tragstruktur (3) im Gehäuse (2) der Turbomaschine (1) vorgesehen ist, daß diese ringför­ mige Tragstruktur (3) im Gehäuse drehbar gelagert und in wenigstens einer Position verriegelbar ist und daß auf ihr alle periodisch zu über­ prüfenden oder auszuwechselnden Baugruppen (5) montiert sind.1. turbomachine with a housing in which a rotor is mounted and which contains the assemblies, such as combustion chambers, cooling systems, etc., characterized in that an annular support structure ( 3 ) is provided in the housing ( 2 ) of the turbomachine ( 1 ), that this ringför shaped support structure ( 3 ) is rotatably mounted in the housing and can be locked in at least one position and that all of the modules ( 5 ) to be checked or replaced periodically are mounted on it. 2. Turbomaschine nach Anspruch 1, dadurch gekennzeichnet, daß die ringförmige Tragstruktur (3) mit einer Einrichtung verbunden ist, welche die ringförmige Tragstruktur (3) bei Bedarf in diverse Arbeitspositionen dreht.2. Turbo machine according to claim 1, characterized in that the annular support structure ( 3 ) is connected to a device which rotates the annular support structure ( 3 ) in various working positions if necessary. 3. Turbomaschine nach Anspruch 2, dadurch gekennzeichnet, daß die Ein­ richtung zum Drehen der ringförmigen Tragstruktur (3) zwischen dem Gehäuse (2) und der ringförmigen Tragstruktur (3) oder zwischen dieser und dem Rotor (4) angeordnet ist.3. Turbo machine according to claim 2, characterized in that a direction for rotating the annular support structure ( 3 ) between the housing ( 2 ) and the annular support structure ( 3 ) or between this and the rotor ( 4 ) is arranged. 4. Turbomaschine nach einem der Ansprüche 1 bis 3, dadurch gekennzeich­ net, daß im Gehäuse (2) der Turbomaschine wenigstens eine verschließ­ bare Montageöffnung (6) vorgesehen ist zum Austausch oder der Über­ prüfung von im Gehäuse (2) angeordneten Baugruppen (5) der Turbo­ maschine.4. Turbo machine according to one of claims 1 to 3, characterized in that in the housing ( 2 ) of the turbomachine at least one lockable bare mounting opening ( 6 ) is provided for exchanging or checking of in the housing ( 2 ) arranged modules ( 5 ) the turbo machine. 5. Turbomaschine nach Anspruch 4, dadurch gekennzeichnet, daß bei mehreren Montageöffnungen (6) diese im wesentlichen in zwei Ebenen angeordnet sind, welche den im Innern des Gehäuses (2) vorhandenen Baugruppen (5) entsprechen.5. Turbo machine according to claim 4, characterized in that in the case of a plurality of assembly openings ( 6 ) these are arranged essentially in two planes which correspond to the assemblies ( 5 ) present in the interior of the housing ( 2 ).
DE1997119770 1997-05-10 1997-05-10 Turbine machine Withdrawn DE19719770A1 (en)

Priority Applications (4)

Application Number Priority Date Filing Date Title
DE1997119770 DE19719770A1 (en) 1997-05-10 1997-05-10 Turbine machine
GB9808224A GB2328477A (en) 1997-05-10 1998-04-17 Access to subassemblies of a turbomachine
CN 98107968 CN1199132A (en) 1997-05-10 1998-05-08 Turbomachine
JP12590898A JPH10317913A (en) 1997-05-10 1998-05-08 Turbine machine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE1997119770 DE19719770A1 (en) 1997-05-10 1997-05-10 Turbine machine

Publications (1)

Publication Number Publication Date
DE19719770A1 true DE19719770A1 (en) 1998-11-12

Family

ID=7829186

Family Applications (1)

Application Number Title Priority Date Filing Date
DE1997119770 Withdrawn DE19719770A1 (en) 1997-05-10 1997-05-10 Turbine machine

Country Status (4)

Country Link
JP (1) JPH10317913A (en)
CN (1) CN1199132A (en)
DE (1) DE19719770A1 (en)
GB (1) GB2328477A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102009045391A1 (en) 2009-10-06 2011-04-07 Robert Bosch Gmbh Micromechanical structure and method for producing a micromechanical structure

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102012202466B3 (en) * 2012-02-17 2013-07-11 Siemens Aktiengesellschaft Assembly of a turbomachine
US10502057B2 (en) * 2015-05-20 2019-12-10 General Electric Company System and method for blade access in turbomachinery
US20190234310A1 (en) * 2018-01-29 2019-08-01 Pratt & Whitney Canada Corp. Segmented internal fuel manifold

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3214101C2 (en) * 1981-04-17 1984-01-26 Nuovo Pignone S.p.A., Firenze Gas turbine plant
DD253851A1 (en) * 1986-11-20 1988-02-03 Orgreb Inst Kraftwerke ARRANGEMENT FOR CONTROLLING TURBINES, ESPECIALLY STEAM TURBINES
GB2244047A (en) * 1990-05-17 1991-11-20 Rolls Royce Plc Inspection aperture plug assembly
US5473883A (en) * 1993-11-03 1995-12-12 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Compressor turbojet engine whose rotor has a movable upstream stage

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3493212A (en) * 1968-06-24 1970-02-03 Westinghouse Electric Corp Rotary machine apparatus
GB1265717A (en) * 1969-06-10 1972-03-08
US4222708A (en) * 1978-06-26 1980-09-16 General Electric Company Method and apparatus for reducing eccentricity in a turbomachine
US4856968A (en) * 1988-02-02 1989-08-15 Armbruster Joseph M Air circulation device
US4925363A (en) * 1989-02-13 1990-05-15 Westinghouse Electric Corp. Blade ring rollout roller
US5233822A (en) * 1991-01-31 1993-08-10 General Electric Company Method and system for the disassembly of an annular combustor
US5249417A (en) * 1991-09-25 1993-10-05 United Technologies Corporation Method and apparatus to install and remove heavy components

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3214101C2 (en) * 1981-04-17 1984-01-26 Nuovo Pignone S.p.A., Firenze Gas turbine plant
DD253851A1 (en) * 1986-11-20 1988-02-03 Orgreb Inst Kraftwerke ARRANGEMENT FOR CONTROLLING TURBINES, ESPECIALLY STEAM TURBINES
GB2244047A (en) * 1990-05-17 1991-11-20 Rolls Royce Plc Inspection aperture plug assembly
US5473883A (en) * 1993-11-03 1995-12-12 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Compressor turbojet engine whose rotor has a movable upstream stage

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102009045391A1 (en) 2009-10-06 2011-04-07 Robert Bosch Gmbh Micromechanical structure and method for producing a micromechanical structure
US8443671B2 (en) 2009-10-06 2013-05-21 Robert Bosch Gmbh Micromechanical structure and method for manufacturing a micromechanical structure

Also Published As

Publication number Publication date
CN1199132A (en) 1998-11-18
GB9808224D0 (en) 1998-06-17
GB2328477A (en) 1999-02-24
JPH10317913A (en) 1998-12-02

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Legal Events

Date Code Title Description
OM8 Search report available as to paragraph 43 lit. 1 sentence 1 patent law
8127 New person/name/address of the applicant

Owner name: ABB ALSTOM POWER (SCHWEIZ) AG, BADEN, AARGAU, CH

8139 Disposal/non-payment of the annual fee