GB2328477A - Access to subassemblies of a turbomachine - Google Patents
Access to subassemblies of a turbomachine Download PDFInfo
- 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- Withdrawn
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, 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
- F02C7/20—Mounting or supporting of plant; Accommodating heat expansion or creep
-
- 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
- F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
- F01D25/285—Temporary support structures, e.g. for testing, assembling, installing, repairing; Assembly methods using such structures
-
- 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
- F05D2230/00—Manufacture
- F05D2230/70—Disassembly 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).
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)
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)
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)
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)
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. |
-
1997
- 1997-05-10 DE DE1997119770 patent/DE19719770A1/en not_active Withdrawn
-
1998
- 1998-04-17 GB GB9808224A patent/GB2328477A/en not_active Withdrawn
- 1998-05-08 CN CN 98107968 patent/CN1199132A/en active Pending
- 1998-05-08 JP JP12590898A patent/JPH10317913A/en active Pending
Patent Citations (7)
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)
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) |