CN103032104A - Airfoil for turbine system - Google Patents
Airfoil for turbine system Download PDFInfo
- Publication number
- CN103032104A CN103032104A CN2012103672232A CN201210367223A CN103032104A CN 103032104 A CN103032104 A CN 103032104A CN 2012103672232 A CN2012103672232 A CN 2012103672232A CN 201210367223 A CN201210367223 A CN 201210367223A CN 103032104 A CN103032104 A CN 103032104A
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- China
- Prior art keywords
- main body
- airfoil
- limits
- turbine system
- nozzle
- 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.)
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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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
An airfoil (40) for a turbine system is disclosed. The airfoil (40) includes a first body (52) having exterior surfaces defining a first portion of an aerodynamic contour of the airfoil and formed from a first material. The airfoil (40) further includes a second body (64) having exterior surfaces defining a second portion of an aerodynamic contour of the airfoil, the second body (64) coupled to the first body (62) and formed from a second material having a different temperature capability than the first material.
Description
Technical field
Theme disclosed herein relates generally to turbine system, and more specifically, relates to the airfoil for turbine system.
Background technique
Turbine system is widely used in the field such as generating.For example, conventional combustion gas turbine systems comprises compressor segmentation, burner segmentation and at least one turbine section.The compressor segmentation is configured to pressurized air when the segmentation of air stream overcompression machine.Then air flow to the burner segmentation from the compressor segmentation, at burner Air and fuel mix and burning, Heat of Formation gas flow.Hot gas stream is provided to turbine section, and turbine section is by utilizing hot gas stream to provide power for compressor, generator and other various loads from hot gas stream extracting energy.
Various parts such as movable vane and nozzle generally include in each segmentation of turbine system to be used for and the stream interaction of passing through these segmentations.For example, each grade of movable vane and nozzle may extend in the hot gas path of turbine section of turbine system.In the operation period of turbine system, this type of component exposed may face owing to the high temperature in the hot gas path risk of damage in the part in hot gas path.Therefore, this base part needs cooling usually.
Before this for attempting having related to the cooling channel of using movable vane and nozzle interior such as the cooling of the parts of movable vane and nozzle.Cooling fluid flows through these internal cooling channels with the part of the outer surface of cooling movable vane and nozzle.Yet these coolings attempt having multiple shortcoming.For example, in many cases, may be difficult to the cooling channel of some part of manufacturing close enough outer surface in movable vane and nozzle to cool off these surfaces.For example owing to lack the inner space make therein the cooling channel, so the trailing edge place of the airfoil part of movable vane and nozzle or near the surface may especially be difficult to cooling.
Therefore, related domain will need improved hot gas path components.For example, the improved airfoil for the hot gas path components can be favourable.
Summary of the invention
Partly in the following description statement of aspects and advantages of the present invention perhaps can be described obviously from this, perhaps can understand by implementing the present invention.
In one embodiment, a kind of airfoil for turbine system is disclosed.This airfoil comprises the first main body, this first main body have the air mechanics contour that limits airfoil first portion outer surface and formed by the first material.This airfoil also comprises the second main body of the outer surface of the second portion with the air mechanics contour that limits airfoil, and this second main body is connected to the first main body and is formed by the second material, and the second material has the temperature capability different from the first material.
A kind of nozzle of the turbine section for turbine system is disclosed in another embodiment.This nozzle comprises the airfoil with the outer surface that limits air mechanics contour, air mechanics contour be included in extend between the frontier and rear on the pressure side and suction side.Airfoil comprises the first main body, this first main body have the air mechanics contour that limits airfoil first portion outer surface and formed by the first material.Airfoil also comprises the second main body of the outer surface of the second portion with the air mechanics contour that limits airfoil, and the second main body is connected to the first main body and is formed by the second material, and the second material has the temperature capability different from the first material.
With reference to following description and claims, these and other feature of the present invention, aspect and advantage will become better understood.The accompanying drawing that is integrated in this specification and forms the part of specification shows embodiments of the invention, and is used for explaining principle of the present invention with this description.
Description of drawings
Disclose fully and fully for the of the present invention of those skilled in the art, comprise its optimal mode, in specification with reference to the accompanying drawings, set forth, in the accompanying drawings:
Fig. 1 is the schematic representation according to an embodiment's of the present disclosure combustion gas turbine systems;
Fig. 2 is the sectional view according to the turbine section of an embodiment's of the present disclosure combustion gas turbine systems;
Fig. 3 is the close-up cross-sectional view according to all parts of the turbine section of an embodiment's of the present disclosure combustion gas turbine systems;
Fig. 4 is the vertical view cutaway drawing according to an embodiment's of the present disclosure airfoil;
Fig. 5 is the fragmentary, perspective view according to a plurality of nozzles of an embodiment of the present disclosure; And
Fig. 6 is the sectional view according to an embodiment's of the present disclosure nozzle.
List of parts
10 turbine systems
12 compressor segmentations
14 burner segmentations
16 turbine section
18 axles
20 hot gas paths
22 guard shields
24 nozzles
26 movable vanes
31 first order nozzle assemblies
32 first order movable vane assemblies
33 second level nozzle assemblies
34 second level movable vane assemblies
35 third level nozzle assemblies
36 third level movable vane assemblies
40 airfoils
42 shanks
44 end caps
52 on the pressure side
54 suction side
56 leading edges
58 trailing edges
62 first main bodys
64 second main bodys
65 cooling channels
66 second main paragraphs
72 recesses
74 projections
76 openings
78 weld seams
79 cover plates.
Embodiment
To carry out detailed reference to embodiments of the invention now, show in the accompanying drawings wherein one or more examples.Each example provides by the mode that the present invention is made an explanation rather than limits the invention.In fact, to those skilled in the art, it is evident that, do not depart from the scope of the present invention or the situation of spirit under, can make in the present invention many modifications and modification.For example, as an embodiment's part and the feature that illustrates or describe can use with another embodiment, to obtain another embodiment.Therefore, the invention is intended to comprise interior this modification and the modification of scope that falls into claims and equivalent thereof.
Fig. 1 is the schematic representation of combustion gas turbine systems 10.Should be appreciated that turbine system 10 of the present disclosure may not be combustion gas turbine systems 10, and can be any suitable turbine system 10, such as steamturbine system or other suitable system.Combustion gas turbine systems 10 can comprise compressor segmentation 12, burner segmentation 14 and turbine section 16.Compressor segmentation 12 and turbine section 16 can be connected by axle 18.Axle 18 can be single axle or be connected to together to form a plurality of joint sections of axle 18.
Substantially known such as related domain, air or another kind of suitable working fluid flow through compressor segmentation 12 and compression in compressor segmentation 12.Then compression working fluid is supplied to burner segmentation 14, in burner segmentation 14, and compression working fluid and fuel mix and burning, thus form hot combustion gas.After hot combustion gas flow through burner segmentation 14, they can flow in the turbine section 16.
Fig. 2 shows an embodiment according to the part of turbine section 16 of the present disclosure.Hot gas path 20 can be limited in the turbine section 16.Various hot gas path components can be at least partially disposed in the hot gas path 20 such as guard shield 22, nozzle 24 and movable vane 26.
For example, as shown in the figure, turbine section 16 can comprise a plurality of movable vanes 26 and a plurality of nozzle 24.In each be at least partially disposed on hot gas path 20 in a plurality of movable vanes 26 and the nozzle 24.In addition, a plurality of movable vanes 26 and a plurality of nozzle 24 can be arranged in one or more annular arrays, the part in each the limited hot gas path 20 in the annular array.
Should be appreciated that turbine section 16 is not limited to three levels, but any amount of level is all in the scope of the present disclosure and spirit.
Should be appreciated that according to hot gas path components of the present disclosure and be not limited to parts in the turbine section 16.On the contrary, the hot gas path components can be the parts that are at least partially disposed in the fluid path with any other the suitable segmentation that is used for compressor segmentation 12 or system 10.
As further illustrating among Fig. 2 and Fig. 3, each hot gas path components can comprise airfoil 40 such as each nozzle 24 and each movable vane 26.For example, the airfoil 40 of movable vane 26 can stretch out from shank 42, and the airfoil 40 of nozzle 24 then can stretch out from end cap 44.Has the outer surface that limits the cardinal principle air mechanics contour according to airfoil 40 of the present disclosure.For example, outer surface can limit between each comfortable leading edge 56 and the trailing edge 58 extend on the pressure side 52 and suction side 54.
To shown in Figure 6, also can comprise first main body 62 and second main body 64 according to airfoil 40 of the present disclosure such as Fig. 3.Each main body 62,64 can limit the part of the outer surface of airfoil 40.Therefore, for example, the first main body 62 can have the outer surface of the first portion of the air mechanics contour that limits airfoil 40, and the second main body 64 has the outer surface of the second portion of the air mechanics contour that limits airfoil 40.
In the exemplary embodiment, the outer surface of the first main body 62 can limit on the pressure side 52 and at least a portion and the leading edge 56 of suction side 54, and the outer surface of the second main body 64 can limit trailing edge 58.The outer surface of the second main body 64 also can limit on the pressure side 52 and the remainder of suction side 54, and perhaps these whole sides can be limited by the first main body 62.Yet in other embodiments, the first main body 62 can comprise restriction on the pressure side 52, any one or a plurality of or their outer surface of any part in suction side 54, leading edge 56 and the trailing edge 58, and the second main body 64 can comprise the outer surface that limits remaining these sides and/or edge or their part.
Formed by the first material according to the first main body 62 of the present disclosure.The first material can be any suitable material, for example suitable metal or metal alloy.For example, in certain embodiments, the first material can comprise aluminium, nickel, iron, carbon, chromium and/or any other suitable metal.It is also understood that the first material is not limited to metal, but the first material can be formed by any suitable material.
In addition, in exemplary embodiment as shown in Figure 4, the first main body 62 can limit one or more cooling channels 65 therein.Cooling channel 65 can be substantial linear or bending, and the extensible any suitable part of passing through the first main body 62.For example, in certain embodiments, cooling channel 65 can be serpentine cooling channel roughly.Such cooling channel 65 can provide the convection current cooling, impact the cooling of cooling and/or any other appropriate format.
The second main body 64 according to airfoil 40 of the present disclosure is formed by the second material.Have the temperature capability different from the first material according to the second material of the present disclosure.Before being illustrated in and losing efficacy, stands temperature capability the ability of uniform temperature, so that the inefficacy of material occurs under such temperature.Therefore, lost efficacy under the temperature of the temperature of the second material when being different from the first material failure.In the exemplary embodiment, the second material has the temperature capability of the temperature capability that is higher than the first material.
The second material can be any suitable metal or metal alloy as discussed above, or suitable nonmetallic material, alloy or composite material.For example, in the exemplary embodiment, the second material is ceramic substrate compound (" CMC ") material.The CMC material is designed to stand the temperature that relatively increases, such as in the such temperature of the operation period of system 10 in hot gas path 20.The CMC material is formed by the ceramic fiber that is embedded in the ceramic substrate usually.Fiber and/or matrix can be formed by carbon, silicon carbide, aluminium oxide, mullite or any other suitable material.If the second material has the temperature capability higher than the first material, then form the second main body 64 with CMC material or other the second suitable material and can advantageously allow the during operation temperature in heated gas path 20 of the second main body 64.Therefore, can not need to cool off the second main body 64.This therein the second main body 64 comprise among the embodiment of trailing edge 58 of airfoil 40 especially favourable, in such embodiments, owing in airfoil 40, lack the inner space that is used for making cooling channel or other suitable cooling unit, so during operation, trailing edge 58 can be cooled off originally fully.
Should be appreciated that the main body that is formed by the first material or the second material can comprise with the layer covering of the first or second material or other material that can only be formed by the first or second material.
In some exemplary embodiments, as shown in Figure 4, the second main body 64 is continuous in whole cross-sectional shape.Therefore, the second main body 64 has solid substantially inside, does not wherein have therein passage or other boring or aperture.Yet, in other embodiments, can limit suitable passage, boring or aperture by the second main body 64 or its part.
In addition, in certain embodiments, the second main body 64 can be single one-piece element.Yet in other embodiment as shown in Figure 3, the second main body 64 can comprise a plurality of the second body segment 66.Each segmentation 66 can be formed by the second material.Should be appreciated that the second material for each segmentation 66 can change or identical.Segmentation 66 can be stacking each other on general radial direction, as shown in the figure, perhaps can otherwise be adjacent to each other to form the second main body 64.With a plurality of the second body segment 66 form the second main body 64 can advantageously allow the second main body 64 before the operation of system 10, during and afterwards because temperature variation in hot gas path 20 and heat increases.
To shown in Figure 6, the second main body 64 can be connected to the first main body 62 such as Fig. 4.When being linked together, the second main body 64 and the first main body 62 can form the cardinal principle air mechanics contour of airfoil 40.
For example, in certain embodiments, in the first main body 62 and the second main body 64 one can limit in recess 72, the first main bodys 62 and the second main body 64 another and then limit engagement protrusion 74.For example, as shown in Figure 4, recess 72 can be the dovetails recess, and projection 74 is the dovetails projection.Yet should be appreciated that the disclosure is not limited to dovetails, but any suitable matrix and convex part all can consist of recess 72 and projection 74.The joint of projection 74 in recess 72 can make them be combined together that the first main body 62 is connected to the second main body 64, as shown in the figure.
In other embodiments, end cap 44 or other suitable coupling arrangement can be connected to the first main body 62 with the second main body 64.For example, as shown in Figure 5 and Figure 6, end cap 44 can comprise and is limited to wherein to be used for the first main body 62 and both openings 76 of the second main body 64.The first main body 62 and the second main body 64 can relative to each other be located, so that they are linked together by end cap 44, as shown in the figure.Being arranged on the first main body 62 in the opening 76 and the part of the second main body 64 can be fixed in the opening.For example, as shown in the figure, weld seam 78 can cover opening 76 or cover plate 79 is fixed to opening 76 so that the first main body 62 and the second main body 64 are fixed on the end cap 44.
Should be appreciated that the disclosure is not limited to be connected to for the second main body 64 with airfoil 40 recess and projection or the end cap of the first main body 62.But any suitable design of the suitable coupling arrangement that main body or be used for is linked together main body is all in the scope of the present disclosure and spirit.
This written description openly comprises the present invention of optimal mode with example, and makes those skilled in the art can implement the present invention, comprises making and using any equipment or system and carry out any method that is included.Patentable scope of the present invention is limited by claim, and can comprise other example that those skilled in the art expect.If comprising from the literal language of claims, this other example do not have different structural elements, if perhaps they comprise and the literal language of the claims equivalent structure element without essential difference, then this other example intention within the scope of the appended claims.
Claims (20)
1. airfoil that is used for turbine system, described airfoil comprises:
The first main body, described the first main body have the air mechanics contour that limits described airfoil first portion outer surface and formed by the first material; With
The second main body, described the second main body has the outer surface of the second portion of the air mechanics contour that limits described airfoil, described the second main body is connected to described the first main body and is formed by the second material, and described the second material has the temperature capability different from described the first material.
2. airfoil according to claim 1 is characterized in that, described the second material is ceramic matrix composites.
3. airfoil according to claim 1 is characterized in that, the outer surface of described the first main body limits at least in part on the pressure side with suction side and also limits leading edge, and wherein, the outer surface of described the second main body limits trailing edge.
4. airfoil according to claim 1 is characterized in that, described the second main body is continuous on whole cross-sectional shape.
5. airfoil according to claim 1 is characterized in that, described the second main body comprises a plurality of the second body segment, and each in described the second body segment is formed by the second material.
6. airfoil according to claim 1, it is characterized in that, one in described the first main body or described the second main body limits recess, and another in described the first main body or described the second main body comprises projection, and wherein, the joint of described projection in described recess is connected to described the first main body with described the second main body.
7. airfoil according to claim 1 is characterized in that, also comprises the end cap that described the second main body is connected to described the first main body.
8. airfoil according to claim 1 is characterized in that, described the first main part limitation cooling channel.
9. nozzle that is used for the turbine section of turbine system, described nozzle comprises:
Airfoil, described airfoil have the outer surface that limits air mechanics contour, described air mechanics contour be included in extend between the frontier and rear on the pressure side and suction side, described airfoil comprises:
The first main body, described the first main body have the air mechanics contour that limits described airfoil first portion outer surface and formed by the first material; With
The second main body, described the second main body has the outer surface of the second portion of the air mechanics contour that limits described airfoil, described the second main body is connected to described the first main body and is formed by the second material, and described the second material has the temperature capability different from described the first material.
10. nozzle according to claim 9 is characterized in that, described the second material is ceramic matrix composites.
11. nozzle according to claim 9 is characterized in that, the outer surface of described the first main body limits at least in part on the pressure side with suction side and also limits leading edge, and wherein, the outer surface of described the second main body limits trailing edge.
12. nozzle according to claim 9 is characterized in that, described the second main body is continuous on whole cross-sectional shape.
13. nozzle according to claim 9, it is characterized in that, one in described the first main body or described the second main body limits recess, and another in described the first main body or described the second main body comprises projection, and wherein, the joint of described projection in described recess is connected to described the first main body with described the second main body.
14. nozzle according to claim 9 is characterized in that, also comprises the end cap that described the second main body is connected to described the first main body.
15. a turbine system comprises:
Turbine section, described turbine section comprises a plurality of hot gas path components, in described a plurality of hot gas path components at least one comprises the airfoil with the outer surface that limits air mechanics contour, described air mechanics contour be included in extend between the frontier and rear on the pressure side and suction side, described airfoil comprises:
The first main body, described the first main body have the air mechanics contour that limits described airfoil first portion outer surface and formed by the first material; With
The second main body, described the second main body has the outer surface of the second portion of the air mechanics contour that limits described airfoil, described the second main body is connected to described the first main body and is formed by the second material, and described the second material has the temperature capability different from described the first material.
16. turbine system according to claim 15 is characterized in that, described the second material is ceramic matrix composites.
17. turbine system according to claim 15 is characterized in that, the outer surface of described the first main body limits at least in part on the pressure side with suction side and also limits leading edge, and wherein, the outer surface of described the second main body limits trailing edge.
18. turbine system according to claim 15 is characterized in that, described the second main body is continuous on whole cross-sectional shape.
19. turbine system according to claim 15, it is characterized in that, one in described the first main body or described the second main body limits recess, and another in described the first main body or described the second main body comprises projection, and wherein, the joint of described projection in described recess is connected to described the first main body with described the second main body.
20. turbine system according to claim 15 is characterized in that, also comprises the end cap that described the second main body is connected to described the first main body.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US13/268087 | 2011-10-07 | ||
| US13/268,087 US20130089431A1 (en) | 2011-10-07 | 2011-10-07 | Airfoil for turbine system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN103032104A true CN103032104A (en) | 2013-04-10 |
Family
ID=46968092
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2012103672232A Pending CN103032104A (en) | 2011-10-07 | 2012-09-28 | Airfoil for turbine system |
Country Status (3)
| Country | Link |
|---|---|
| US (1) | US20130089431A1 (en) |
| EP (1) | EP2578807A2 (en) |
| CN (1) | CN103032104A (en) |
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| CA2917967A1 (en) | 2013-07-09 | 2015-01-15 | United Technologies Corporation | Plated polymer compressor |
| EP3019710A4 (en) | 2013-07-09 | 2017-05-10 | United Technologies Corporation | Plated polymer fan |
| CA2917879A1 (en) | 2013-07-09 | 2015-01-15 | United Technologies Corporation | Metal-encapsulated polymeric article |
| WO2015053832A2 (en) * | 2013-07-09 | 2015-04-16 | United Technologies Corporation | High-modulus coating for local stiffening of airfoil trailing edges |
| WO2015017095A2 (en) | 2013-07-09 | 2015-02-05 | United Technologies Corporation | Plated polymer nosecone |
| WO2015075239A1 (en) | 2013-11-25 | 2015-05-28 | Alstom Technology Ltd | Blade assembly on basis of a modular structure for a turbomachine |
| CN106103901B (en) | 2013-12-20 | 2019-04-16 | 安萨尔多能源英国知识产权有限公司 | Rotor blade or guide vane assembly |
| WO2015191041A1 (en) * | 2014-06-10 | 2015-12-17 | Siemens Energy, Inc. | Trailing edge insert for an airfoil within a gas turbine engine |
| US10626740B2 (en) | 2016-12-08 | 2020-04-21 | General Electric Company | Airfoil trailing edge segment |
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- 2012-10-05 EP EP12187542.1A patent/EP2578807A2/en not_active Withdrawn
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Also Published As
| Publication number | Publication date |
|---|---|
| US20130089431A1 (en) | 2013-04-11 |
| EP2578807A2 (en) | 2013-04-10 |
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Application publication date: 20130410 |