CN204344286U - Turbine assembly and turbine system - Google Patents
Turbine assembly and turbine system Download PDFInfo
- Publication number
- CN204344286U CN204344286U CN201420445998.1U CN201420445998U CN204344286U CN 204344286 U CN204344286 U CN 204344286U CN 201420445998 U CN201420445998 U CN 201420445998U CN 204344286 U CN204344286 U CN 204344286U
- Authority
- CN
- China
- Prior art keywords
- flange
- projection
- turbine
- stator module
- movable vane
- 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 - Fee Related
Links
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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
-
- 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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Gasket Seals (AREA)
Abstract
The utility model relates to the system and method that the stream between space is taken turns in minimizing or restriction hot gas passage and turbine.A kind of turbine assembly is disclosed herein.Turbine assembly can comprise rotor, and this rotor is with at least one movable vane radially extended from it.Turbine assembly also can comprise stator module, contiguous at least one movable vane location of stator module.In addition, turbine assembly can comprise black box.Black box can comprise the first flange, and it extends along basic axial direction from least one movable vane.Black box also can comprise the second flange, and itself and the first flange extend along basic axial direction from stator module on the contrary.Second flange can comprise towards at least one outstanding projection of the first flange.
Description
Technical field
Embodiment of the present disclosure relates generally to gas turbine engine, and relates more particularly to the system and method for the one or more streams between the wheel space for reducing or be limited in hot-gas channel and turbine.
Background technique
Gas turbine engine typically comprises compressor, burner and turbine.The efficiency portion ground of turbine depends on the amount of the cooling-air stream from compressor, and cooling-air stream is used for the parts in the hot-gas channel in cooling turbine section.Cooling-air stream can be introduced in the wheel space of turbine, enters in wheel space to limit high-temperature gas.Wheel space temperature can be increased to the excessive suction stream in wheel space and exceed material property by hot gas, thus causes material to exceed temperature limiting, and this can facilitate rotor creep and/or break.On the other hand, flow to wheel space and can reduce turbine efficiency with the excessive cooling-air stoping hot gas to suck and/or purge stream, because the merit that cooling-air stream may not be suitable for whole turbine produces.
Model utility content
Some or all in above demand and/or problem are solved by some embodiment of the present disclosure.According to an embodiment, disclose a kind of turbine assembly.This turbine assembly can comprise rotor, and this rotor has at least one movable vane radially extended from it.This turbine assembly also can comprise stator module, and this stator module has at least one fixed nozzle stator blade of contiguous at least one movable vane location.In addition, turbine assembly can comprise black box.Black box can comprise the first flange, and it extends along basic axial direction from least one movable vane.Sealing assembly also can comprise the second flange, and itself and the first flange extend along basic axial direction from stator module on the contrary.Second flange can comprise towards at least one outstanding projection of the first flange.
According to another embodiment, disclose a kind of turbine system.This system can comprise compressor.This system also can comprise the combustion system be communicated with compressor.In addition, this system can comprise the turbine be communicated with combustion system.Turbine can comprise rotor, and this rotor has at least one movable vane radially extended from it.This turbine also can comprise stator module, and it has at least one fixed nozzle stator blade of contiguous at least one movable vane location.In addition, turbine can comprise black box.Black box can comprise the first flange, and it extends along basic axial direction from least one movable vane.Black box also can comprise the second flange, and itself and the first flange extend along basic axial direction from stator module on the contrary.Second flange can comprise towards at least one outstanding projection of the first flange.
In addition, according to another embodiment, disclose a kind of minimizing or limit the method for leading to the wheel space of turbine and the stream of hot-gas channel.The method can comprise around at least one movable vane of being positioned by the first flange radially to extend from rotor.In addition, the method can comprise and is positioned around stator module by the second flange, contiguous at least one movable vane location of this stator module.First flange and the second flange radially spaced apartly can be at least partially formed black box.In addition, the method can comprise the stream utilizing at least one projection of giving prominence to from the second flange towards the first flange to reduce wheel space towards turbine and hot-gas channel.
According to the following detailed description, accompanying drawing and claims, other embodiment, aspect and feature of the present invention will become apparent to those skilled in the art.
Accompanying drawing explanation
To make reference to accompanying drawing now, accompanying drawing may not be drawn in proportion.
Fig. 1 schematically draws the example views of the gas turbine assembly according to embodiment of the present disclosure.
Fig. 2 schematically draws the example views of a part for the turbine assembly according to embodiment of the present disclosure.
Fig. 3 schematically draws the example views according to the black box in the turbine assembly of embodiment of the present disclosure.
Fig. 4 schematically draws the example views according to the black box in the turbine assembly of embodiment of the present disclosure.
Fig. 5 schematically draws the example views according to the black box in the turbine assembly of embodiment of the present disclosure.
Embodiment
Present general more fully describe illustrative embodiment, more shown in the drawings instead of all embodiments with reference to accompanying drawing hereinafter.The disclosure can many different forms embody, and should not be construed as the embodiment being limited to and setting forth in literary composition.In the text, identical label represents identical element.
Fig. 1 illustrates the schematic diagram of the gas turbine engine 10 that can be used for herein.Gas turbine engine 10 can comprise compressor 15.The inlet flow of compressor 15 pressurized air 20.The compressive flow of air 20 is sent to burner 25 by compressor.The compressive flow of the compressive flow of air 20 and fuel 30 mixes by burner 25, and puts burning mixt to form combustion gas stream 35.Although only illustrate burner 25, this gas turbine engine 10 can comprise the burner 25 of any amount.Combustion gas stream 35 is sent to the turbine 40 in downstream successively.Combustion gas stream 35 drives turbine 40 to produce mechanical work.The mechanical work produced in turbine 40 drives compressor 15 and external load 50, such as generator etc. via 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 any one in some different gas turbine engines, such as provided by the General Electric Co. Limited of Si Kanaitadi city, New York (Schenectady, New York) those, etc.Gas turbine engine 10 can have different configurations, and can use the parts of other types.Also the gas turbine engine of other types can be used at this.Also the turbine of multiple gas turbine engine, other types and the power generating equipment of other types can be used together at this.
Fig. 2 schematically draws an example embodiment of a part for turbine 40.Turbine 40 can comprise the rotor 52 around longitudinal axis location.Some movable vanes 54 can be mounted to rotor 52.Such as, movable vane 54 can circumferentially be spaced apart from each other, and extends radially outwardly from rotor 52.Movable vane 54 can form one or more levels in turbine 40.Movable vane 54 can have shank 56 and airfoil 58.
Fixing shell 60 can be arranged around movable vane 54, thinks that combustion gas stream 35 limits the hot gas path running through turbine 40.In addition, some stator modules 62 can be close to movable vane 54 and locate.Such as, stator module 62 can be positioned upstream and/or the downstream of each movable vane 54.Each in stator module 62 can have fixing nozzle stator blade.Wheel space 66 can be formed between each stator module 62 and movable vane 54.
Black box 68 can be positioned between each stator module 62 and movable vane 54.Black box 68 can stop, reduces and/or limit combustion gas stream 35 and enter wheel space 66.In addition, black box 68 can reduce the amount that restriction hot gas enters the purging air of wheel needed for space 66 and/or cooling-air.
Black box 68 can comprise the first flange 70, and this first flange 70 extends along basic axial direction from movable vane 54.In some cases, the first flange 70 can be angel's wing Sealing (angel wing seal).First flange 70 axially can extend from the upstream of the shank 56 of movable vane 54 and/or downstream surface.In some cases, the first flange 70 can end at the top 72 extended radially outwardly, and it can comprise tooth or fin.In other situation, the top 72 extended radially outwardly can be omitted.
Black box also can comprise the second flange 74, and this second flange 74 and the first flange 70 extend along basic axial direction from stator module 62 on the contrary.In some cases, the second flange 74 can be baffle seal.The baffle seal of arbitrary number can be used at this.Second flange 74 axially can extend from the upstream of stator module 62 and/or downstream surface.In some cases, the second flange 74 is positioned the radially outer of the first flange 70.Such as, the second flange 74 can be radially spaced apart with the first flange 70, to form gap between.Other parts and other configuration can be used at this.
Fig. 3 draws the example embodiment of the black box 100 that can use in this article.Black box 100 can comprise the first flange 102 extended from the shank 56 of movable vane 54.In some cases, the first flange 102 can be angel's wing Sealing.Such as, the first flange 102 can end at the top 104 extended radially outwardly.In other situation, the top 104 extended radially outwardly can be omitted.Black box 100 also can comprise the second flange 106 extended from stator module 62.In some cases, the second flange 106 can be baffle seal.Second flange 106 can comprise towards at least one outstanding projection 108 of the first flange 102.In some cases, at least one projection 108 can be arranged at around the far-end 110 of the second flange 106.At least one projection 108 can comprise towards some outstanding projections of the first flange 102.At least one projection 108 can be tooth, the wing, projection, fin or its combination.Other parts and other configuration can be used at this.At least one projection 108 and the first flange 102 can cooperate to limit more tortuous passage and pass for cool stream, and the hot gas that restriction enters in wheel space sucks.In some cases, the second flange 106 can insert in stator module 62.In other situation, the second flange 106 can be clogged, be welded on stator module 62 or formed the integral part of stator module 62.
Fig. 4 draws the example embodiment of the black box 112 that can use in this article.Black box 112 can comprise the first flange 114 extended from the shank 56 of movable vane 54.In some cases, the first flange 114 can be angel's wing Sealing.Such as, the first flange 114 can end at the top 116 extended radially outwardly.In other situation, the top 116 extended radially outwardly can be omitted.Black box 112 also can comprise the second flange 118 extended from stator module 62.In some cases, the second flange 118 can be baffle seal.Second flange 118 can comprise towards at least one outstanding projection 120 of the first flange 114.At least one projection 120 can comprise towards some outstanding projections of the first flange 114.In some cases, between at least one projection 120 far-end 122 that can be arranged at the second flange 118 and stator module 62.At least one projection 120 can be tooth, the wing, projection, fin or its combination.Other parts and other configuration can be used at this.At least one projection 120 and the first flange 114 can cooperate to limit more tortuous passage and pass for cool stream, and the hot gas that restriction enters wheel space sucks.In some cases, the second flange 118 can insert in stator module 62.In other situation, the second flange 118 can be clogged, be welded on stator module 62 or form the integral part of stator module 62.
Fig. 5 draws the example embodiment of the black box 124 that can use in this article.Black box 124 can comprise the first flange 126 extended from the shank 56 of movable vane 54.In some cases, the first flange 126 can be angel's wing Sealing.Such as, the first flange 126 can end at the top 128 extended radially outwardly.In other situation, the top 128 extended radially outwardly can be omitted.Black box 124 also can comprise the second flange 130 extended from stator module 62.In some cases, the second flange 130 can be baffle seal.Second flange 130 can comprise from least one outstanding projection 132 of the far-end 134 of the second flange 130.In some cases, at least one projection 132 can comprise two projections extended in opposite direction.Such as, in one embodiment, the second flange 130 and at least one projection 132 can form T-shaped component jointly.In other situation, at least one projection 132 in axial direction can extend on the contrary with the first flange 126.At least one projection 132 can comprise some projections.At least one projection 132 can be tooth, the wing, projection, fin or its combination.Miscellaneous part and other configurations can be used at this.At least one projection 132 and the first flange 126 can cooperate to limit more tortuous passage and pass for cool stream, and the hot air that restriction enters wheel space sucks.In some cases, the second flange 130 can insert in stator module 62.In other situation, the second flange 130 can be clogged, be welded on stator module 62 or form the integral part of stator module 62.
Can stop, reduce and/or limit combustion gas stream 35 from the projection of the second flange extension and enter wheel space 66.In addition, the projection extended from the second flange can stop, reduce and/or limit purging air and/or cooling-air enters hot gas path.Second flange can comprise the multiple projections outstanding along various direction.Such as, the second flange can comprise be arranged at the second flange far-end around one or more projections, one or more projections between the far-end being arranged on the second flange and stator module, in axial direction combine from the outstanding one or more projection of the far-end of the second flange and/or its on the contrary with the first flange.
Although to have described in words embodiment for structure characteristic and/or method behavior, should be understood that the disclosure need not be limited to described specific features or behavior.But concrete feature and behavior are disclosed as the illustrative form carrying out embodiment.Such as, the various embodiments described in Fig. 1 to 5 can be in conjunction with.That is, the second flange can comprise the multiple projections outstanding along various direction.
Claims (16)
1. a turbine assembly, comprising:
Rotor;
At least one movable vane, it radially extends from described rotor;
Stator module, contiguous described at least one movable vane location; And
Black box, it comprises:
First flange, it extends along basic axial direction from least one movable vane described; With
Second flange, itself and described first flange extend along basic axial direction from described stator module on the contrary, and wherein said second flange comprises towards at least one outstanding projection of described first flange.
2. turbine assembly according to claim 1, is characterized in that, at least one projection described is arranged at around the far-end of described second flange.
3. turbine assembly according to claim 1, is characterized in that, between the far-end that at least one projection described is arranged at described second flange and described stator module.
4. turbine assembly according to claim 1, is characterized in that, also comprises second at least one projection, and itself and described first flange are given prominence to along described basic axial direction from the far-end of described second flange on the contrary.
5. turbine assembly according to claim 1, is characterized in that, described second flange comprises baffle seal.
6. turbine assembly according to claim 1, is characterized in that, described first flange comprises angel's wing Sealing.
7. turbine assembly according to claim 1, is characterized in that, described first flange and described second flange limit gap between which.
8. turbine assembly according to claim 1, is characterized in that, at least one projection described comprises one or more tooth, the wing, projection or fin.
9. a turbine system, comprising:
Compressor;
The combustion system be communicated with described compressor;
The turbine be communicated with described combustion system, wherein said turbine comprises:
Rotor;
At least one movable vane, it radially extends from described rotor;
Stator module, its contiguous described at least one movable vane location; And
Black box, it comprises:
First flange, it extends along basic axial direction from least one movable vane described; With
Second flange, itself and described first flange extend along basic axial direction from described stator module on the contrary, and wherein said second flange comprises towards at least one outstanding projection of described first flange.
10. system according to claim 9, is characterized in that, at least one projection described is arranged at around the far-end of described second flange.
11. systems according to claim 9, is characterized in that, between the far-end that at least one projection described is arranged at described second flange and described stator module.
12. systems according to claim 9, is characterized in that, also comprise second at least one projection, and itself and described first flange are given prominence to along described basic axial direction from the far-end of described second flange on the contrary.
13. systems according to claim 9, is characterized in that, described second flange comprises baffle seal.
14. systems according to claim 9, is characterized in that, described first flange comprises angel's wing Sealing.
15. systems according to claim 9, is characterized in that, described first flange and described second flange limit gap between which.
16. systems according to claim 9, is characterized in that, at least one projection described comprises one or more tooth, the wing, projection or fin.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US13/962,244 US20150040567A1 (en) | 2013-08-08 | 2013-08-08 | Systems and Methods for Reducing or Limiting One or More Flows Between a Hot Gas Path and a Wheel Space of a Turbine |
| US13/962244 | 2013-08-08 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204344286U true CN204344286U (en) | 2015-05-20 |
Family
ID=52388987
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420445998.1U Expired - Fee Related CN204344286U (en) | 2013-08-08 | 2014-08-08 | Turbine assembly and turbine system |
Country Status (5)
| Country | Link |
|---|---|
| US (1) | US20150040567A1 (en) |
| JP (1) | JP2015034547A (en) |
| CN (1) | CN204344286U (en) |
| CH (1) | CH708448A2 (en) |
| DE (1) | DE102014111201A1 (en) |
Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102013220276A1 (en) * | 2013-10-08 | 2015-04-09 | MTU Aero Engines AG | flow machine |
| DE102015224259A1 (en) * | 2015-12-04 | 2017-06-08 | MTU Aero Engines AG | Run-on surface for vane cover and blade base plate |
| DE102015224379A1 (en) * | 2015-12-04 | 2017-06-08 | MTU Aero Engines AG | Stabilized sealing ring for a turbomachine |
| KR102525225B1 (en) * | 2021-03-12 | 2023-04-24 | 두산에너빌리티 주식회사 | Turbo-machine |
| US11459903B1 (en) | 2021-06-10 | 2022-10-04 | Solar Turbines Incorporated | Redirecting stator flow discourager |
Family Cites Families (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4218189A (en) * | 1977-08-09 | 1980-08-19 | Rolls-Royce Limited | Sealing means for bladed rotor for a gas turbine engine |
| US5749701A (en) * | 1996-10-28 | 1998-05-12 | General Electric Company | Interstage seal assembly for a turbine |
| SE507745C2 (en) * | 1996-11-05 | 1998-07-06 | Alfa Laval Ab | sealing device |
| JP3327814B2 (en) * | 1997-06-18 | 2002-09-24 | 三菱重工業株式会社 | Gas turbine sealing device |
| US6779972B2 (en) * | 2002-10-31 | 2004-08-24 | General Electric Company | Flowpath sealing and streamlining configuration for a turbine |
| US7287956B2 (en) * | 2004-12-22 | 2007-10-30 | General Electric Company | Removable abradable seal carriers for sealing between rotary and stationary turbine components |
| US20060275108A1 (en) * | 2005-06-07 | 2006-12-07 | Memmen Robert L | Hammerhead fluid seal |
| US20060275107A1 (en) * | 2005-06-07 | 2006-12-07 | Ioannis Alvanos | Combined blade attachment and disk lug fluid seal |
| US7540709B1 (en) * | 2005-10-20 | 2009-06-02 | Florida Turbine Technologies, Inc. | Box rim cavity for a gas turbine engine |
| US7500824B2 (en) * | 2006-08-22 | 2009-03-10 | General Electric Company | Angel wing abradable seal and sealing method |
| US20080145208A1 (en) * | 2006-12-19 | 2008-06-19 | General Electric Company | Bullnose seal turbine stage |
| US9309783B2 (en) * | 2013-01-10 | 2016-04-12 | General Electric Company | Seal assembly for turbine system |
| JP6078353B2 (en) * | 2013-01-23 | 2017-02-08 | 三菱日立パワーシステムズ株式会社 | gas turbine |
-
2013
- 2013-08-08 US US13/962,244 patent/US20150040567A1/en not_active Abandoned
-
2014
- 2014-08-06 JP JP2014159962A patent/JP2015034547A/en active Pending
- 2014-08-06 DE DE102014111201.6A patent/DE102014111201A1/en not_active Withdrawn
- 2014-08-07 CH CH01205/14A patent/CH708448A2/en not_active Application Discontinuation
- 2014-08-08 CN CN201420445998.1U patent/CN204344286U/en not_active Expired - Fee Related
Also Published As
| Publication number | Publication date |
|---|---|
| DE102014111201A1 (en) | 2015-02-12 |
| JP2015034547A (en) | 2015-02-19 |
| US20150040567A1 (en) | 2015-02-12 |
| CH708448A2 (en) | 2015-02-13 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20150520 Termination date: 20180808 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |