GB2328477A - Access to subassemblies of a turbomachine - Google Patents

Access to subassemblies of a turbomachine Download PDF

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Publication number
GB2328477A
GB2328477A GB9808224A GB9808224A GB2328477A GB 2328477 A GB2328477 A GB 2328477A GB 9808224 A GB9808224 A GB 9808224A GB 9808224 A GB9808224 A GB 9808224A GB 2328477 A GB2328477 A GB 2328477A
Authority
GB
United Kingdom
Prior art keywords
turbomachine
casing
subassemblies
supporting structure
annular supporting
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Withdrawn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
GB9808224A
Other versions
GB9808224D0 (en
Inventor
Urs Benz
Hans-Jurgen 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.)
ABB Asea Brown Boveri Ltd
ABB AB
Original Assignee
ABB Asea Brown Boveri Ltd
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 ABB Asea Brown Boveri Ltd, Asea Brown Boveri AB filed Critical ABB Asea Brown Boveri Ltd
Publication of GB9808224D0 publication Critical patent/GB9808224D0/en
Publication of GB2328477A publication Critical patent/GB2328477A/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Withdrawn legal-status Critical Current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)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Hydraulic Turbines (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

A turbomachine has a casing 2 in which a rotor 4 is mounted and an annular supporting structure 3 provided in the casing on which subassemblies 5, such as combustion chambers and cooling systems are mounted. The annular supporting structure 3 is rotatably mounted in the casing 2 and can be locked in at least one position. When subassemblies 5 require checking or exchanging the annular supporting structure 3 may be rotated into inspection or assembly positions where they are accessible through closable assembly openings 6 in the casing 2. More than one closable assembly opening 6 may be present.

Description

2328477
TITLE OF THE INVENTION Turbomachine
BACKGROUND OF THE INVENTION 5 Field of the Invention
The invention relates to a according to the preamble of patent claim 1.
Discussion of Backcround turbomachine In turbomachines, subassemblies have to be regularly checked or dismantled and replaced in connection with maintenance work. To this end, it is generally necessary for the top part, the top half shell of the casing of the turbomachine, to be removed in order to gain access to these subassemblies. Such partial dismantling is very complicated and timeconsuming and therefore expensive; often only to find, in particular, that the checked subassemblies continue to be serviceable. In addition, such partial dismantling requires an excessive amount of assembly time compared with the actual inspection time.
SUMVIARY OF THE INVENTION Accordingly, one object of the invention, in attempting to avoid all of these disadvantages, is to provide a novel turbomachine in which partial dismantling is not necessary to the previous extent in order to check or exchange subassemblies.
This object is achieved by the features of the defining part of patent claim 1. Advantageous embodiments of a turbomachine are specified by the features of the dependent claims.
BRIEF DESCRIPTION OF THE DRAWINGS
A more complete appreciation of the invention and many of the attendant advantages thereof will be readily obtained as the same becomes better understood by reference to the following detailed description when - 2 considered in connection with the accompanying drawings, wherein:
Fig. 1 schematically shows part of the casing of a turbomachine, partly in local section; Fig. 2 schematically shows a partial section (AA) through the turbomachine perpendicularly to its axis.
only the elements essential for understanding the invention are shown; in particular, that part of the turbomachine which is unaltered and is known per se or any of its other details, etc., are not shown.
DESCRIPTION OF THE PREFERRED EMBODIMENTS
Referring now to the drawings, wherein like reference numerals designate identical or corresponding parts throughout the several views, in a turbomachine 1 having a casing 2, in which a rotor 4 is mounted and which contains the peripheral subassemblies, such as combustion chambers, cooling systems, etc., an annular supporting structure 3 is provided in the casing 2. This annular supporting structure 3 is rotatably mounted in the casing and can be locked in at least one position. All the subassemblies 5 which are to be checked or exchanged periodically are mounted on it. In order to be able to rotate the annular supporting structure 3 into various assembly or inspection positions when required during an inspection of the turbomachine 1, it is connected to a device which, on the one hand, locks the annular supporting structure 3 in the operating position and, on the other hand, moves it into the requisite assembly or inspection positions. This device for rotating the annular supporting structure 3 is arranged between the casing 2 and the annular supporting structure 3 or between the latter and the rotor 4. The casing 2 of the turbomachine 1 has at least one closable assembly opening 6, which has such a size and shape that the subassemblies 5 of the turbomachine 1 which are to be checked or replaced easily accessible or can easily be dismantled are and 3 removed. In particular, if there is a plurality of assembly openings 6, they are arranged essentially in two planes which are normal to the axis and which correspond to the subassemblies 5 present in the 5 interior of the casing 2. This ensures that the subassemblies 5 of the turbomachine are accessible, as a result of which the downtime is substantially reduced. In addition, in the case of a turbomachine designed in such a way, the casing no longer needs to be partly dismantled in order to gain access to the subassemblies 5 which are to be replaced or checked. This produces substantial savings during the inspection.
Obviously, numerous modifications and variations of the present invention are possible in light of the above teachings. It is therefore to be understood that, within the scope of the appended claims, the invention may be practiced otherwise than as specifically described herein.

Claims (5)

1. A turbomachine having a casing in which a rotor is mounted and which contains the subassemblies, such as combustion chambers, cooling systems, etc., wherein an annular supporting structure (3) is provided in the casing (2) of the turbomachine (1), this annular supporting structure (3) is rotatably mounted in c-he casing and can be locked in at least one position, and all the subassemblies (5) which are to be checked or exchanged periodically are mounted on it.
2. The turbomachine as claimed in claim 1, wherein the annular supporting structure (3) is connected to a device which rotates the annular supporting structure (3) into various working positions when required.
3. 1 The turbomachine as claimed in claim 2, wherein the device for rotating the annular supporting structure (3) is arranged between the casing (2) and the annular supporting structure (3) or between the latter and the rotor (4).
4. The turbomachine as claimed in one of claims 1 to 3, wherein at least one closable assembly opening (6) is provided in the casing (2) of the turbomachine in order to exchange or check subassemblies (5) of the turbomachine which are arranged in the casing (2).
5. The turbomachine as claimed in claim 4, wherein, if there is a plurality of assembly openings (6), they are arranged essentially in two planes which correspond to the subassemblies (5) present in the interior of the casing (2).
GB9808224A 1997-05-10 1998-04-17 Access to subassemblies of a turbomachine Withdrawn GB2328477A (en)

Applications Claiming Priority (1)

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

Publications (2)

Publication Number Publication Date
GB9808224D0 GB9808224D0 (en) 1998-06-17
GB2328477A true GB2328477A (en) 1999-02-24

Family

ID=7829186

Family Applications (1)

Application Number Title Priority Date Filing Date
GB9808224A Withdrawn GB2328477A (en) 1997-05-10 1998-04-17 Access to subassemblies of a turbomachine

Country Status (4)

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

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3095970A1 (en) * 2015-05-20 2016-11-23 General Electric Company System and method for blade access in turbomachinery
EP3521591A1 (en) * 2018-01-29 2019-08-07 Pratt & Whitney Canada Corp. Semented internal fuel manifold

Families Citing this family (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
DE102012202466B3 (en) * 2012-02-17 2013-07-11 Siemens Aktiengesellschaft Assembly of a turbomachine

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1211313A (en) * 1968-06-24 1970-11-04 Westinghouse Electric Corp Bladed elastic fluid handling machine
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
GB2228051A (en) * 1989-02-13 1990-08-15 Westinghouse Electric Corp Rotary machine casings
EP0497519A1 (en) * 1991-01-31 1992-08-05 General Electric Company Method and system for the disassembly of an annular combustor
WO1993006343A1 (en) * 1991-09-25 1993-04-01 United Technologies Corporation Method and apparatus to install and remove heavy components

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
IT1135752B (en) * 1981-04-17 1986-08-27 Nuovo Pignone Spa IMPROVEMENTS IN THE POWER STAGE OF A GAS TURBINE
DD253851A1 (en) * 1986-11-20 1988-02-03 Orgreb Inst Kraftwerke ARRANGEMENT FOR CONTROLLING TURBINES, ESPECIALLY STEAM TURBINES
GB2244047B (en) * 1990-05-17 1994-02-16 Rolls Royce Plc Inspection aperture sealing
FR2712037B1 (en) * 1993-11-03 1995-12-08 Snecma Compressor turbomachine, the rotor of which has a removable upstream stage.

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1211313A (en) * 1968-06-24 1970-11-04 Westinghouse Electric Corp Bladed elastic fluid handling machine
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
GB2228051A (en) * 1989-02-13 1990-08-15 Westinghouse Electric Corp Rotary machine casings
EP0497519A1 (en) * 1991-01-31 1992-08-05 General Electric Company Method and system for the disassembly of an annular combustor
WO1993006343A1 (en) * 1991-09-25 1993-04-01 United Technologies Corporation Method and apparatus to install and remove heavy components

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3095970A1 (en) * 2015-05-20 2016-11-23 General Electric Company System and method for blade access in turbomachinery
CN106168164A (en) * 2015-05-20 2016-11-30 通用电气公司 For the system and method close to the blade in turbine
US10502057B2 (en) 2015-05-20 2019-12-10 General Electric Company System and method for blade access in turbomachinery
EP3521591A1 (en) * 2018-01-29 2019-08-07 Pratt & Whitney Canada Corp. Semented internal fuel manifold

Also Published As

Publication number Publication date
JPH10317913A (en) 1998-12-02
GB9808224D0 (en) 1998-06-17
CN1199132A (en) 1998-11-18
DE19719770A1 (en) 1998-11-12

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Legal Events

Date Code Title Description
WAP Application withdrawn, taken to be withdrawn or refused ** after publication under section 16(1)