CN104769235A - Gas turbine engine exhaust system and corresponding method for accessing turbine buckets - Google Patents
Gas turbine engine exhaust system and corresponding method for accessing turbine buckets Download PDFInfo
- Publication number
- CN104769235A CN104769235A CN201280076814.2A CN201280076814A CN104769235A CN 104769235 A CN104769235 A CN 104769235A CN 201280076814 A CN201280076814 A CN 201280076814A CN 104769235 A CN104769235 A CN 104769235A
- Authority
- CN
- China
- Prior art keywords
- vent systems
- systems according
- diffusion device
- exhaust frame
- front portion
- 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.)
- Pending
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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
- 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
- F01D25/243—Flange connections; Bolting arrangements
-
- 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
- F01D25/30—Exhaust heads, chambers, or the like
-
- 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
-
- 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
- F05D2260/00—Function
- F05D2260/02—Transport and handling during maintenance and repair
Abstract
According to one embodiment, there is disclosed an exhaust system for a gas turbine engine. The system may include an inner diffuser section having a forward portion and an aft portion. The system may also include a circumferential groove disposed in the aft portion. Moreover, the system may include a boss disposed in the forward portion. In this manner, the boss may be configured to mate with the circumferential groove to attach the forward portion to the aft portion in a removable configuration. A corresponding method for accessing turbine buckets is also provided.
Description
Technical field
Embodiments of the invention relate in general to gas turbine engine, and relate more specifically to vent systems and the method for promoting to enter one or more turbine blade.
Background technique
Gas turbine engine is widely used in the fields such as such as generating.Conventional gas turbogenerator can comprise compressor, burner and turbo machine.Compressor can supply pressurized air to burner, and in the burner, pressurized air also can burn to generate hot gas with fuel mix.This hot gas can be provided to turbo machine, in the turbine, can extract energy to produce merit from hot gas.Specifically, turbo machine can comprise and passing therethrough along with hot gas and the one or more turbine blade rotated.Hot gas leaves turbo machine by vent systems.
But typical exhaust system configuration essence hinders close to turbine blade to carry out keeping in repair and/or replacing.Therefore, the performance not destroying gas turbine engine close to turbine blade is made to be still matter of utmost importance.
Summary of the invention
More than to need and/or part or all of problem solves by some embodiment of the present invention.According to an embodiment, the present invention discloses a kind of vent systems for gas turbine engine.Described system can comprise the interior diffuser section with front and rear.Described system also can comprise the circumferential recess be arranged in described rear portion.In addition, described system can comprise the boss be arranged in described front portion.In this way, described boss is configurable is attached to described rear portion with removable configuration by described front portion for coordinating with described circumferential recess.
According to another embodiment, the present invention discloses a kind of vent systems for gas turbine engine.Described system can comprise the interior diffuser section with front and rear.Described system also can comprise groove and tongue joint (rabbet joint), and described groove and tongue joint arrangement is used for front portion to be attached to rear portion.
In addition, according to another embodiment, the present invention disclose a kind of for entering/close to the method for one or more turbine blade.Described method can comprise and removes exhaust frame front shell.Described method also can comprise the front portion removing external diffusion device section.In addition, described method can comprise the front portion removing interior diffuser section.
For one of skill in the art, other embodiments of the present invention, aspect and feature will be apparent from following detailed description, accompanying drawing and appended claims.
Accompanying drawing explanation
With reference to accompanying drawing, accompanying drawing also need not be drawn in proportion, and in the accompanying drawings:
Fig. 1 is the illustrative diagram with the gas turbine engine of compressor, burner and turbo machine according to an embodiment of the invention.
Fig. 2 is the cross-sectional view of a part for vent systems according to an embodiment of the invention.
Fig. 3 is the cross-sectional view of a part for vent systems according to an embodiment of the invention.
Embodiment
More fully describe illustrative embodiment of the present invention with reference to accompanying drawing following, in the accompanying drawings, the embodiment of part of the present invention but not all is shown.The present invention is by much multi-form enforcement and should not be considered as being limited to the embodiment set forth in this specification; On the contrary, the object of these embodiments is provided to be to meet applicable law requirement.In the accompanying drawings, similar numeral refers to like.
Exemplary embodiment relates to the gas turbine engine that comprises vent systems among other things and for promoting the method close to one or more turbine blade.In this way, some embodiment of the present invention promotes close to one or more turbine blade, especially afterbody turbine blade by vent systems.Such as, the various parts described by this specification from vent systems dismounting and/or can remove.That is, in one embodiment, exhaust frame front shell, the front portion of external diffusion device section and the front portion of interior diffuser section can be removed, so as to make close/enter (or removing) afterbody turbine blade.
In one exemplary embodiment, vent systems of the present invention can comprise the interior diffuser section with front and rear.In some cases, the front portion of interior diffuser section and the rear portion of interior diffuser section are attached each other removedly by groove and tongue joint.Such as, groove and tongue joint can comprise circumferential recess in the rear portion being arranged on interior diffuser section and be arranged on the boss in the front portion of interior diffuser section.In this way, boss is configurable for coordinating with circumferential recess.In certain embodiments, retaining ring can be close to circumferential recess location, to be fixed in circumferential recess by boss.
In some cases, vent systems of the present invention also can comprise primary seal, and the contiguous circumferential recess location of described primary seal, seals to be formed between exhaust frame and interior diffuser section.Such as, slit can be associated with the rear portion of interior diffuser section, can be arranged in slit at least partially with what make primary seal.In other cases, vent systems can comprise time Sealing, the location, front end of the front portion of diffuser section in described time Sealing is contiguous.Secondary Sealing can be formed and seal between exhaust frame and interior diffuser section.Such as, slit can be associated with the front portion of interior diffuser section, is arranged in slit at least partially with what make time Sealing.
In certain embodiments, vent systems can comprise external diffusion device section, and described external diffusion device section has the front portion being attached to rear portion.In other embodiments, vent systems can comprise exhaust frame front shell, and described exhaust frame front shell is arranged around interior diffuser section and external diffusion device section.Such as, exhaust frame front shell can be included in one end attachment (such as, bolt) to turbine casing and be attached to the shell of exhaust frame at the other end.In other embodiments, vent systems can comprise outside front Sealing, and before described outside, the location, front end of the front portion of Sealing contiguous external diffusion device section, seals to be formed between exhaust frame front shell and external diffusion device section.
Go to Fig. 1 now, Fig. 1 describes the schematic diagram as the exemplary embodiment of gas turbine engine 10 spendable in this specification.Such as, gas turbine engine 10 can comprise compressor 15.Compressor 15 is compressible enters air stream 20.Compressor 15 can carry pressurized air stream 20 to burner 25.Pressurized air stream 20 can mix with pressurized flow 30 by burner 25, then puts burning mixt to produce combustion-gas flow 35.Although only illustrate a burner 25, gas turbine engine 10 can comprise the burner 25 of any number.Combustion-gas flow 35 is delivered to again turbo machine 40 then.Combustion-gas flow 35 can drive turbo machine 40 to produce mechanical work.The mechanical work produced in turbo machine 40 drives the external loading 50 such as compressor 15 and such as generator by axle 45.
Gas turbine engine 10 can use the fuel of rock gas, various types of synthetic gas and/or other types.Gas turbine engine 10 can be General Electric Co. Limited (the General Electric Company of Schenectady in Si Kanaita city, New York, New York) any one of multiple different gas turbine engine that provides, include, but is not limited to 7 series or 9 series heavy-duty gas turbine engines etc. those.Gas turbine engine 10 can have different configuration and can use other types parts.In addition, the gas turbine engine of other types can also be used in this manual.In this manual, also can use the turbo machine of multiple gas turbine engine, other types and the power generating equipment of other types simultaneously.
The partial view of the exemplary embodiment of gas turbine engine 10 is described with reference to figure 2, Fig. 2.In one embodiment, gas turbine engine 10 can comprise vent systems 100.Vent systems 100 can comprise exhaust frame 102.Such as, exhaust frame 102 can support the various parts of (directly or indirectly) vent systems 100.Vent systems 100 also can comprise exhaust frame front shell 104.In some cases, exhaust frame front shell 104 can at one end be attached (such as, by bolt 106) to turbine casing 108, and is attached to exhaust frame 102 at the other end.In one embodiment, exhaust frame front shell 104 can be formed by some parts, two 180 degree of shells that described parts are such as fixed together.But in other embodiments, exhaust frame front shell 104 can be single parts or multiple parts.In this way, exhaust frame front shell 104 can disassemble from turbine casing 108 and exhaust frame 102, to make the inside close to vent systems 100.
Vent systems 100 also can comprise external diffusion device section 110.External diffusion device section 110 can comprise rear portion 112 and anterior 114.In some cases, when assembling, the front portion 114 of the rear portion 112 of external diffusion device section 110 and external diffusion device section 110 can be fixed together (such as, by bolt 116) to form the continuous flow path of burning hot gas.In addition, vent systems 100 can comprise outside front Sealing 118, between the front portion 114 that before described outside, Sealing 118 is positioned in external diffusion device section 110 and exhaust frame front shell 104.Before outside, Sealing 118 can be remained in appropriate location by the radial slit 120 be associated with the front portion 114 of external diffusion device section 110 and the radial slit 122 be associated with exhaust frame front shell 104.Any fixation method can be used to be fastened in appropriate location by Sealing before outside 118.
In some cases, in order to make close/enter the inside of vent systems 100, Sealing 118 before outside can be removed from radial slit 120 and 122.In addition, the rear portion 112 of the front portion 114 of external diffusion device section 110 from external diffusion device section 110 can be disassembled and remove.
In one embodiment, vent systems 100 can comprise interior diffuser section 124.Inside and outside diffuser section 124 can comprise rear portion 126 and anterior 128.In some cases, when assembling, the front portion 128 of the rear portion 126 of interior diffuser section 124 and interior diffuser section 124 can be fixed together to form the continuous flow path of burning hot gas by groove and tongue joint 130.As Fig. 2 and Fig. 3 describe, in one embodiment, groove and tongue joint 130 can comprise the circumferential recess 132 in the rear portion 128 being arranged on interior diffuser section 124.In addition, groove and tongue joint 130 can comprise the boss 134 in the front portion 126 being arranged on interior diffuser section 124.In this way, boss 134 is configurable for coordinating with circumferential recess 132, such as, coordinates in the mode of clasp joint.In certain embodiments, vent systems 100 also can comprise retaining ring 136, and the contiguous circumferential recess 132 of described retaining ring 136 and boss 134 are located, to be fixed in circumferential recess 132 by boss 134.
In some cases, vent systems 100 can comprise primary seal 138, and the contiguous circumferential recess 132 of described primary seal 138 is located, and seals to be formed between exhaust frame 102 and interior diffuser section 124.Such as, primary seal 138 can be fixed in appropriate location by the radial slit 140 be associated with the rear portion 126 of interior diffuser 124 and the bolt 142 be associated with exhaust frame 102.But, any fixation method can be used to be fastened in appropriate location by primary seal 138.In other instances, vent systems 100 can comprise time Sealing 144, and in described time Sealing 144 is contiguous, the location, front end of the front portion 128 of diffuser section 124, seals to be formed between exhaust frame 102 and interior diffuser section 124.In the exemplary embodiment, secondary Sealing can be fixed in appropriate location by the axial slots 146 associated with the front portion 128 of interior diffuser section 124 and the radial slit 148 be associated with removable ring 150.
The front portion 128 of interior diffuser section 124 is by removing from vent systems 100 with under type: remove retaining ring 136, and makes the front portion 128 of interior diffuser section 124 depart from from primary seal 138 and time Sealing 144 subsequently.In addition, removable ring 150 can be removed to make to enter/close to chamber 152 to carry out removing of turbine blade 154.Such as, exhaust frame front shell 104, the front portion 114 of external diffusion device section 11, the front portion 128 of interior diffuser section 124 and the removable of removable ring 150 provide space, are drawn out impeller of rotor to carry out maintenance and/replacement to allow afterbody turbine blade 154 on rear side of turbine cylinder.
Although describe embodiment with the language specific to structure characteristic and/or method operation, should be appreciated that, the present invention is not necessarily limited to described concrete feature or operation.On the contrary, concrete characteristic sum operation is disclosed as the illustrative form realizing embodiment.
Claims (20)
1., for a vent systems for gas turbine engine, described vent systems comprises:
Interior diffuser section, described interior diffuser section comprises front and rear;
Be arranged on the circumferential recess in described rear portion; And
Be arranged on the boss in described front portion, described boss is configured to coordinate with described circumferential recess thus with removable structure, described front portion be attached to described rear portion.
2. vent systems according to claim 1, described vent systems comprises retaining ring further, and the contiguous described circumferential recess location of described retaining ring, to be fixed on described boss in described circumferential recess.
3. vent systems according to claim 1, described vent systems comprises primary seal further, and the contiguous described circumferential recess location of described primary seal, seals to be formed between exhaust frame and described interior diffuser section.
4. vent systems according to claim 3, described vent systems comprises the slit be associated with described rear portion further, being arranged at least partially in described slit of wherein said primary seal.
5. vent systems according to claim 1, described vent systems comprises time Sealing further, and the location, front end of described the contiguous described front portion of Sealing, seals to be formed between exhaust frame and described interior diffuser section.
6. vent systems according to claim 5, described vent systems comprises the slit be associated with the described front end of described front portion further, being arranged at least partially in described slit of wherein said Sealing.
7. vent systems according to claim 1, described vent systems comprises external diffusion device section further, and described external diffusion device section comprises front and rear.
8. vent systems according to claim 7, described vent systems comprises exhaust frame front shell further, and described exhaust frame front shell is arranged around described interior diffuser section and described external diffusion device section.
9. vent systems according to claim 8, described vent systems comprises outside front Sealing further, before described outside, the location, front end of the described front portion of the contiguous described external diffusion device section of Sealing, seals to be formed between described exhaust frame front shell and described external diffusion device section.
10., for a vent systems for gas turbine engine, described vent systems comprises:
Interior diffuser section, described interior diffuser section comprises front and rear; And
Groove and tongue joint, described groove and tongue joint arrangement is used for described front portion to be attached to described rear portion.
11. vent systems according to claim 10, wherein said groove and tongue joint comprises:
Be arranged on the circumferential recess in described rear portion; And
Be arranged on the boss in described front portion, described boss is configured to coordinate that described front portion is attached to described rear portion with described circumferential recess.
12. vent systems according to claim 11, described vent systems comprises retaining ring further, and the contiguous described circumferential recess location of described retaining ring, to be fixed on described boss in described circumferential recess.
13. vent systems according to claim 11, described vent systems comprises primary seal further, and the contiguous described circumferential recess location of described primary seal, seals to be formed between exhaust frame and described interior diffuser section.
14. vent systems according to claim 13, described vent systems comprises the slit be associated with described rear portion further, being arranged at least partially in described slit of wherein said primary seal.
15. vent systems according to claim 10, described vent systems comprises time Sealing further, and the location, front end of described the contiguous described front portion of Sealing, seals to be formed between exhaust frame and described interior diffuser section.
16. vent systems according to claim 15, described vent systems comprises the slit be associated with the described front end of described front portion further, being arranged at least partially in described slit of wherein said Sealing.
17. vent systems according to claim 10, described vent systems comprises external diffusion device section further, and described external diffusion device section comprises front and rear.
18. vent systems according to claim 17, described vent systems comprises exhaust frame front shell further, and described exhaust frame front shell is arranged around described interior diffuser section and described external diffusion device section.
19. vent systems according to claim 18, described vent systems comprises outside front Sealing further, before described outside, the location, front end of the described front portion of the contiguous described external diffusion device section of Sealing, seals to be formed between described exhaust frame front shell and described external diffusion device section.
20. 1 kinds for entering the method for one or more turbine blade, described method comprises:
Remove exhaust frame front shell;
Remove the front portion of external diffusion device section; And
Remove the front portion of interior diffuser section.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| PCT/IB2012/002841 WO2014068355A1 (en) | 2012-10-30 | 2012-10-30 | Gas turbine engine exhaust system and corresponding method for accessing turbine buckets |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104769235A true CN104769235A (en) | 2015-07-08 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201280076814.2A Pending CN104769235A (en) | 2012-10-30 | 2012-10-30 | Gas turbine engine exhaust system and corresponding method for accessing turbine buckets |
Country Status (2)
| Country | Link |
|---|---|
| CN (1) | CN104769235A (en) |
| WO (1) | WO2014068355A1 (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107035443A (en) * | 2015-11-24 | 2017-08-11 | 通用电气公司 | The system for supporting turbine diffuser |
| CN108350753A (en) * | 2015-12-24 | 2018-07-31 | 三菱日立电力系统株式会社 | Method for dismounting, apparatus for carrying out the method and the fixture of blade, the blade assembly for having the device |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP6441611B2 (en) * | 2014-08-25 | 2018-12-19 | 三菱日立パワーシステムズ株式会社 | Gas turbine exhaust member and exhaust chamber maintenance method |
| EP3441578B1 (en) * | 2017-08-11 | 2021-03-03 | General Electric Company | Turbine exhaust diffuser |
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| US4391566A (en) * | 1979-11-14 | 1983-07-05 | Nissan Motor Co., Ltd. | Diffuser and exhaust gas collector arrangement |
| US5104286A (en) * | 1991-02-08 | 1992-04-14 | Westinghouse Electric Corp. | Recirculation seal for a gas turbine exhaust diffuser |
| US5346365A (en) * | 1992-09-25 | 1994-09-13 | Asea Brown Boveri Ltd. | Gas turbine with exhaust gas casing and exhaust gas duct |
| JP2004011609A (en) * | 2002-06-11 | 2004-01-15 | Toshiba Corp | Steam turbine |
| CN1594845A (en) * | 2003-09-11 | 2005-03-16 | Snecma发动机公司 | Provision of sealing for the cabin-air bleed cavity using a segment seal |
| CN1692250A (en) * | 2003-07-14 | 2005-11-02 | 三菱重工业株式会社 | Cooling structure of gas turbine tail pipe |
| US20070160471A1 (en) * | 2006-01-11 | 2007-07-12 | United Technologies Corporation | Split flange V-groove and anti-rotation mating system |
| CN101372904A (en) * | 2007-08-23 | 2009-02-25 | 通用电气公司 | Method, system and apparatus for turbine diffuser sealing |
| CN102121480A (en) * | 2009-12-31 | 2011-07-13 | 通用电气公司 | Systems and apparatus relating to compressor stator blades and diffusers in turbine engines |
-
2012
- 2012-10-30 WO PCT/IB2012/002841 patent/WO2014068355A1/en active Application Filing
- 2012-10-30 CN CN201280076814.2A patent/CN104769235A/en active Pending
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4391566A (en) * | 1979-11-14 | 1983-07-05 | Nissan Motor Co., Ltd. | Diffuser and exhaust gas collector arrangement |
| US5104286A (en) * | 1991-02-08 | 1992-04-14 | Westinghouse Electric Corp. | Recirculation seal for a gas turbine exhaust diffuser |
| US5346365A (en) * | 1992-09-25 | 1994-09-13 | Asea Brown Boveri Ltd. | Gas turbine with exhaust gas casing and exhaust gas duct |
| JP2004011609A (en) * | 2002-06-11 | 2004-01-15 | Toshiba Corp | Steam turbine |
| CN1692250A (en) * | 2003-07-14 | 2005-11-02 | 三菱重工业株式会社 | Cooling structure of gas turbine tail pipe |
| CN1594845A (en) * | 2003-09-11 | 2005-03-16 | Snecma发动机公司 | Provision of sealing for the cabin-air bleed cavity using a segment seal |
| US20070160471A1 (en) * | 2006-01-11 | 2007-07-12 | United Technologies Corporation | Split flange V-groove and anti-rotation mating system |
| CN101372904A (en) * | 2007-08-23 | 2009-02-25 | 通用电气公司 | Method, system and apparatus for turbine diffuser sealing |
| CN102121480A (en) * | 2009-12-31 | 2011-07-13 | 通用电气公司 | Systems and apparatus relating to compressor stator blades and diffusers in turbine engines |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107035443A (en) * | 2015-11-24 | 2017-08-11 | 通用电气公司 | The system for supporting turbine diffuser |
| CN107035443B (en) * | 2015-11-24 | 2021-12-10 | 通用电气公司 | System for supporting a turbine diffuser |
| CN108350753A (en) * | 2015-12-24 | 2018-07-31 | 三菱日立电力系统株式会社 | Method for dismounting, apparatus for carrying out the method and the fixture of blade, the blade assembly for having the device |
| CN108350753B (en) * | 2015-12-24 | 2020-07-10 | 三菱日立电力系统株式会社 | Blade disassembling method, disassembling device, clamp and blade assembly |
Also Published As
| Publication number | Publication date |
|---|---|
| WO2014068355A1 (en) | 2014-05-08 |
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Application publication date: 20150708 |