CN104704202A - Turbine blades with platform cooling and corresponding gas turbine - Google Patents
Turbine blades with platform cooling and corresponding gas turbine Download PDFInfo
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- CN104704202A CN104704202A CN201380051904.0A CN201380051904A CN104704202A CN 104704202 A CN104704202 A CN 104704202A CN 201380051904 A CN201380051904 A CN 201380051904A CN 104704202 A CN104704202 A CN 104704202A
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- platform
- cooling circuit
- pressure side
- suction side
- shock surface
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- 238000001816 cooling Methods 0.000 title claims abstract description 93
- 239000002826 coolant Substances 0.000 claims abstract description 39
- 239000012530 fluid Substances 0.000 claims abstract description 37
- 230000035939 shock Effects 0.000 claims description 54
- 239000000567 combustion gas Substances 0.000 claims description 9
- 230000037361 pathway Effects 0.000 claims description 9
- 241001328961 Aleiodes compressor Species 0.000 claims 1
- 239000007789 gas Substances 0.000 description 9
- 230000000694 effects Effects 0.000 description 4
- 238000000034 method Methods 0.000 description 4
- 230000005540 biological transmission Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000006872 improvement Effects 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 238000011144 upstream manufacturing Methods 0.000 description 2
- 239000000654 additive Substances 0.000 description 1
- 230000000996 additive effect Effects 0.000 description 1
- 230000008901 benefit Effects 0.000 description 1
- 238000005266 casting Methods 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 238000003801 milling Methods 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
Classifications
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- 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
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/08—Heating, heat-insulating or cooling means
- F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
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- 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
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/187—Convection cooling
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- 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
- F05D2240/00—Components
- F05D2240/80—Platforms for stationary or moving blades
- F05D2240/81—Cooled platforms
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- 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
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/205—Cooling fluid recirculation, i.e. after cooling one or more components is the cooling fluid recovered and used elsewhere for other purposes
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
A turbine blade generally includes a platform having a pressure side, a suction side, a leading edge, a trailing edge, a pressure side slash face and a suction side slash face. A platform cooling circuit extends within the platform. The platform cooling circuit may extend from the suction side of the platform to the pressure side of the platform. The platform cooling circuit generally defines a fluid flow path that directs a cooling medium from the platform suction side to the platform pressure side.
Description
Technical field
The platform of relate generally to cooling turbomachine blade of the present invention.More specifically, the present invention relates to the platform cooling circuit of the fluid flow path on the pressure side limited from the suction side of platform to platform.
Background technique
Turbo machine is widely used for such as generating electricity etc. in field.Conventional gas turbo machine can usually comprise compressor, burner and turbo machine.In operation, the various parts experience temperature flowing in combustion gas turbine, this can cause component failure.Because the flowing of higher temperature causes the performance of combustion gas turbine, efficiency and power stage to increase usually, the parts of experience temperature flowing must be cooled combustion gas turbine can be operated at increased temperature.
The various strategies cooling various gas turbine engine component are become known in related domain.Such as, cooling medium can be provided to various parts from compressor transmission.Additive method can comprise the replaceable cooling medium of transmission (such as steam) by the various parts in combustion gas turbine.In the compressor and turbine section of system, cooling medium may be used for cooling various compressor and turbine components.
Turbine bucket is an example of the hot gas path parts that must be cooled.Such as, the various parts (such as, aerofoil profile, platform, shank and afterbody) of turbine bucket to be arranged in hot gas path and to be exposed to relative high temperature, therefore need cooling.Various coolant path and cooling circuit can be limited in the various parts of turbine bucket, and cooling medium can flow through various coolant path and cooling circuit with cooling turbomachine blade.
In a lot of known turbines blade, a part for turbine bucket can reach the temperature higher than other parts of turbine bucket.In known turbines blade, the special concrete region worried is the suction side of platform, and the suction side of this platform is general adjacent with suction side shock surface (slash face) and extend across the trailing edge of platform.Additionally or alternatively, cooling medium can on the pressure side flow to exhaust port the suction side of platform or path from platform.But along with cooling medium is from the pressure side flowing, heat energy is passed to cooling medium, thus flows through along with cooling medium and/or flow through platform and reduce the cooling effect of cooling medium.Therefore, the cooling to suction side can be reduced.
Therefore, the turbine bucket of the useful improvement in turbine system is expected in related domain.Particularly, the turbine bucket with the air-circulation features of improvement can be more favourable.
Summary of the invention
All aspects of of the present invention and advantage will be set forth in the following description, or can be apparent by specification, or can know by implementing the present invention.
One embodiment of the present of invention are a kind of turbine buckets.Turbine bucket usually comprise have on the pressure side, the platform of suction side, leading edge, trailing edge, on the pressure side shock surface and suction side shock surface.Platform cooling circuit extends in platform.Platform cooling circuit can extend to platform on the pressure side from the suction side of platform.Platform cooling circuit usually limits fluid flow path, and cooling medium is guided to plateau pressure side from platform suction side by fluid flow path.
Another embodiment of the present invention is a kind of turbine bucket, and turbine bucket has main body, the main cooling circuit in described main part limitation main body.Platform is at least in part around main body.Main body comprise have on the pressure side, the platform of suction side, leading edge, trailing edge, on the pressure side shock surface (slash face) and suction side shock surface.Platform cooling circuit extends in platform, and is communicated with the main cooling circuit fluid of main body.Platform cooling circuit extends to platform on the pressure side from the suction side of platform in platform.Platform cooling circuit limits fluid flow path, and cooling medium is striden across platform trailing edge from the main cooling circuit of main body and guides to plateau pressure side by fluid flow path.
The present invention can also comprise a kind of combustion gas turbine, and this combustion gas turbine has compressor, the burner in compressor downstream and the turbo machine in burner downstream, and turbo machine has at least one turbine bucket.Platform is at least in part around turbine bucket, and described platform has leading edge, trailing edge, on the pressure side shock surface, suction side shock surface and top surface, and top surface has on the pressure side and suction side.Platform limits one or more outlets of at least one on the pressure side shock surface, suction side shock surface or the top surface extending through platform.Platform cooling circuit extends in platform, and is communicated with at least one outlet fluid.Platform cooling circuit a bit extends to platform on the pressure side along trailing edge from adjacent with suction side shock surface cardinal principle below the top surface of platform.Platform cooling circuit limits fluid flow path, and cooling medium is guided to plateau pressure side from platform suction side and discharges cooling medium by least one outlet by fluid flow path.
After consulting specification, those of ordinary skill in the art will understand the characteristic sum All aspects of of these embodiments and other embodiments better.
Accompanying drawing explanation
In reference the description of the drawings book remainder, more specifically elaboration comprises is the of the present invention complete and enforceable open of optimal mode of the present invention to those skilled in the art, wherein:
Fig. 1 is the schematic diagram of the gas turbine system according to an embodiment of the present disclosure;
Fig. 2 is the perspective view of the turbine bucket according to an embodiment of the present disclosure;
Fig. 3 shows the side view of the inner member of the turbine bucket according to an embodiment of the present disclosure;
Fig. 4 is the top view of the turbine bucket according at least one embodiment of the present disclosure;
Fig. 5 is the side view of the turbine bucket according at least one embodiment of the present disclosure;
Fig. 6 is the top view of the turbine bucket according at least one embodiment of the present disclosure; With
Fig. 7 is the top view of the turbine bucket according at least one embodiment of the present disclosure.
Embodiment
Present general is in detail with reference to embodiments of the invention, and one or more examples of these embodiments are shown in the drawings.Detailed description use numeral and letter character represent the feature in accompanying drawing.In drawing and description, same or similar symbol is for representing identical or like of the present invention.As used herein, term " first ", " second " and " the 3rd " can use to be distinguished from each other out by parts interchangeably, instead of will represent position or the significance of all parts.In addition, term " upstream " and " downstream " represent parts relative position in the fluid passage.Such as, if fluid flows to part B from components A, then components A is in the upstream of part B.On the contrary, if the fluid that part B receives from components A flows, then part B is in the downstream of components A.
Each example is provided as explanation of the present invention instead of as restriction of the present invention.In fact, those skilled in the art do not depart from the scope of the present invention obviously carrying out various modifications and variations in the present invention or spirit.Such as, to illustrate as an embodiment's part or the feature that describes may be used for another embodiment to produce another embodiment.Therefore, the present invention be intended to contain fall into claims and equivalent thereof scope in such modifications and variations.
Various embodiment of the present invention is included in the platform cooling circuit extended below the top surface of turbine bucket platform.Platform cooling circuit usually extends to platform on the pressure side from the suction side of platform.Platform cooling circuit limits fluid flow path at least in part, flows through platform cooling circuit to make cooling medium.One or more outlet can provide the fluid in the hot gas path from platform cooling circuit to turbo machine to be communicated with.In replacement form, at least one outlet can direct cooling medium through the shock surface of turbine bucket.Suction side near the platform of the trailing edge of platform is the high-temperature area that can limit the mechanical life of turbine bucket potentially.The method of current cooling turbomachine blade make cooling medium only along on the pressure side flowing or by cooling medium from the pressure side guiding to suction side.But, show, once cooling medium flows through the high-temperature part on the pressure side of platform, then cooling medium weak effect when cooling suction side.Therefore, by make cooling medium flow to platform on the pressure side before along suction side and along the trailing edge of platform, cooling medium is flowed, the cooling effect that cooling medium strides across suction side can be improved, and simultaneously minimum on the impact of cooling effect of the cooling medium on the pressure side striding across platform.
Fig. 1 is the schematic diagram of combustion gas turbine 10.Combustion gas turbine 10 can comprise compressor 12, burner 14 and turbo machine 16.Compressor 12 and turbo machine 16 can be connected by axle 18.Axle 18 can be that single shaft maybe can comprise the multiple shaft parts being linked together to be formed axle 18.
Turbo machine 16 can comprise at least one-level aerofoil profile (not shown).Every one-level at least in one-level aerofoil profile can generally include a line stator blade and adjacent with this row stator blade and in this row stator blade downstream a line rotary turbine blades.Stator vane can along the circumferential direction arrange around axle 18 and fix.Turbine bucket can be circumferentially spaced apart around the rotor disk being connected to axle 18.Rotor disk can comprise the one or more coolant paths providing and be communicated with turbine bucket fluid.The at different levels of turbo machine 16 can limit hot gas path (not shown) at least in part, and hot gas path guides hot gas from burner 14 by turbo machine 16.Be to be understood that turbo machine 16 is not limited to three levels.Such as, turbo machine 16 can have two, three, a four or more level.Similarly, compressor 12 can comprise multiple compressor stage (not shown).Each level of compressor 12 can comprise the isolated stator vane of multiple circumference and multiple rotatable compressor blades.
Fig. 2 illustrates the perspective view of turbine bucket, and Fig. 3 provides the side view of the inner member that turbine bucket is shown.As shown in Figure 2, turbine bucket 30 can comprise main body 32 and platform 34.Main body 32 generally includes aerofoil profile 36 and shank 38.Aerofoil profile 36 can from platform 34 and/or shank 38 radially outward location.Shank 38 can comprise root 40, and root can be configured to attached rotor disk (not shown), and rotor disk is attached and/or around axle 18.Aerofoil profile 36 generally includes on the pressure side 42 and suction side 44, leading edge 46 and trailing edge 48.In addition, aerofoil profile 36 generally includes root 50 and most advanced and sophisticated 52.The root 50 of aerofoil profile 36 is usually crossing with platform 34.Most advanced and sophisticated 52 usually radially away from root 50.
As shown in Figure 2, platform 34 can at least in part around main body 32.Typical platform 34 can be placed on intersection between the root 50 of the aerofoil profile 36 of main body 32 and shank 38 or transition position.Platform 34 can stretch out from main body 32 substantially vertically He tangentially.But, should be appreciated that the position can according to platform of the present invention with any appropriate.Platform 34 can also comprise leading edge 60, trailing edge 62, on the pressure side shock surface 64 and suction side shock surface 66.The top surface 68 of platform 34 can at least in part platform 34 leading edge 60, trailing edge 62, on the pressure side extend between shock surface 64 and suction side shock surface 66.
Platform 34 usually can be divided on the pressure side 70 and suction side 72.In a particular embodiment, the top surface 68 of platform 34 can limit on the pressure side 70 and suction side 72 of platform 34 at least in part.Aerofoil profile 36 can on the pressure side 70 to separate with the suction side 72 of platform 34 at least in part by platform 34.Such as, platform 34 on the pressure side 70 can be limited at least in part aerofoil profile 36 on the pressure side 42 and platform 34 on the pressure side shock surface 64 at least partially between.The suction side 72 of platform 34 can be limited at least in part the suction side 44 of aerofoil profile 36, the leading edge 60 of platform at least partially, at least partially and between the suction side shock surface 66 of platform 34 of the trailing edge 62 of platform 34.
As shown in Figure 3, one or more internal main cooling circuit 80 can extend through the main body 32 shown in Fig. 3.Main cooling circuit 80 can extend through the various parts of main body 32 to provide one or more fluid flow path, thus cooling medium (such as pressurized air or steam) is flowed with cools body 32 and/or aerofoil profile 36 during operation.Such as, in some embodiment as shown in Figure 3, main body 32 can limit front main cooling circuit 82 and rear main cooling circuit 84.Main cooling circuit 80 can have arbitrarily suitably shape, and can along suitably path extension arbitrarily in main body 32 and/or aerofoil profile 36.Such as, each main cooling circuit 80 can have various branch and meanders, and as shown in Figure 3, each main cooling circuit 80 can extend through the various parts of main body 32, such as, by aerofoil profile 36 and shank 38.Cooling medium can enter main cooling circuit 80 by root 40 part of shank 38.
According to various embodiments of the present invention, Fig. 4 provides the top view of turbine bucket, and Fig. 5 provides the side view of turbine bucket, Fig. 6 and Fig. 7 provides the top view of turbine bucket.As shown in Figures 4 to 7, in one or more platform cooling circuit 90 platform 34 that can be limited at turbine bucket 30 and/or main body 32.As shown in Fig. 5, Fig. 6 and Fig. 7, platform cooling circuit 90 can be limited in platform 34 at least in part.Such as, in the exemplary embodiment, a part for platform cooling circuit 90 is limited in platform 34, and extends through platform 34 to cool this platform 34.As shown in the figure, platform cooling circuit 90 usually extends below the top surface 68 of platform 34.Other parts of platform cooling circuit 90 can extend in main body 32 and/or aerofoil profile 36.
In at least one embodiment, as shown in Figure 4, platform cooling circuit 90 can comprise entrance 92, suction side part 94 and pressure-side portion 96.Entrance 92 can be connected at least one the main cooling circuit 80 extending through main body 32 and/or aerofoil profile 36 by fluid.Such as, entrance 92 can fluid to be connected in front main cooling circuit 82 and rear main cooling circuit 84 any one or respectively fluid be connected to both.In a particular embodiment, entrance 92 can be arranged on below the top surface 68 of platform 34, is positioned at least in part in the suction side 66 of platform 34.Such as, entrance 92 can be arranged in platform 34, in the suction side 44 of aerofoil profile 36 and between the suction side shock surface 66 of platform 34 and trailing edge 62.
The suction side 66 that the suction side part 94 of platform cooling circuit 90 usually strides across platform 34 from entrance 92 extends.In a particular embodiment, as shown in Figure 4, the suction side 66 of platform cooling circuit 90 can usually from entrance 92 towards the extension at least partially of suction side shock surface 66, and/or at least in part with suction side shock surface 66 be adjacent at least partially extend.Suction side part 94 then can stride across the trailing edge 62 of platform 34 from suction side shock surface 66 and the on the pressure side shock surface 64 towards platform 34 extends.Suction side part 94 can usually extend with the trailing edge 62 of platform 34 abreast.Additionally or alternatively, suction side shock surface 66 can stride across the suction side 66 one or many reverses direction of platform 34.Crossing over below aerofoil profile 36 along with platform cooling circuit 90 and/or extend on the pressure side 70 of platform 34 around aerofoil profile 36, the suction side part 94 of platform cooling circuit 90 is roughly transitioned into pressure-side portion 96.
The pressure-side portion 96 of platform cooling circuit 90 roughly platform 34 on the pressure side 70 top surface 68 below extend.As shown in the figure, pressure-side portion 96 can roughly be adjacent to the on the pressure side shock surface 64 of platform 34 extend towards the leading edge 60 of platform 34.In a particular embodiment, pressure-side portion 96 can along on the pressure side 70 reverses direction at least one times of platform 34.Such as, as shown in the figure, what pressure-side portion 96 can stride across platform 34 on the pressure side 70 has substantially zigzag pattern.
As shown in Figures 5 to 7, at least one outlet 98 can extend through at least one on the pressure side shock surface 64 or suction side shock surface 66.Additionally or alternatively, as shown in Figure 7, at least one outlet 98 can platform 34 on the pressure side 70 and/or suction side 72 on extend through the top surface 68 of platform 34.Such as, as shown in figure 5 and figure 7, at least one outlet 98 can be positioned between the leading edge 46 of aerofoil profile 36 and the leading edge 60 of platform 34.Additionally or alternatively, at least one outlet 98 can platform 34 on the pressure side 70 or suction side 72 at least one on extend through the top surface 68 of platform 34.As shown in Figures 5 to 7, at least one outlet 98 can be connected to the pressure-side portion 96 of platform cooling circuit 90 by fluid.
As shown in Figures 5 to 7, platform cooling circuit 90 and at least one outlet 98 can limit fluid flow path 100 at least in part, to make cooling medium flow on the pressure side 70 of platform 34 from the suction side 72 of platform 34, thus make cooling medium flow in the pressure-side portion 96 of platform cooling circuit 90 before remove heat energy from the suction side 72 of platform 34.As a result, the suction side 72 of platform 34 can be cooled more effectively, thus improves the overall mechanical properties of turbine bucket 30.In a particular embodiment, cooling medium can flow through at least one outlet 98 of locating along on the pressure side shock surface 64 and/or suction side shock surface 66 from platform cooling circuit 90.In this way, cooling medium may be used for shank 38 part and/or on the pressure side shock surface 64 and the suction side shock surface 66 of the main body 32 of further cooling turbomachine blade 30.Additionally or alternatively, as shown in Figure 7, cooling medium can flow through from platform cooling circuit 90 at least one outlet 98 be arranged on the top surface 68 of platform 34, thus provides film cooling to the top surface 68 of platform 34.
In other embodiments, as shown in Figure 6, at least one vent pathway 102 can extend, roughly between the leading edge 46 and the leading edge 60 of platform 34 of aerofoil profile 36 in platform 34 and/or main body 32.Vent pathway 102 can on the pressure side extend between shock surface 64 and suction side shock surface 66 at least in part.In a particular embodiment, vent pathway 102 extends to suction side shock surface 66 from the pressure side shock surface 64.Vent pathway 102 can be limited by platform cooling circuit 90 at least in part.In replacement form, vent pathway 102 can be separated in milling, casting or be otherwise formed in platform 34, with platform cooling circuit 90.Vent pathway 102 can fluid be connected to platform cooling circuit 90 and fluid be connected at least one outlet 98 at least one.Vent pathway 102 can also limit fluid flow path 100.As a result, cooling medium can before being discharged by least one outlet 98, and the region substantially adjacent to the leading edge 60 with platform 34 provides further cooling.
This specification uses example openly to comprise the present invention of optimal mode, and also enables any technician of related domain implement the present invention, comprises and manufactures and use any device or system and perform any method comprised.Patentable scope of the present invention is defined by the claims, and can comprise other example that those skilled in the art expects.Like this other is intended to belong in the scope of claims with example, as long as they have the structural element as broad as long with the word language of these claims, as long as or they comprise and the equivalent structural elements of the word language of this claim without substantive difference.
Claims (20)
1. a turbine bucket, comprising:
A. platform, described platform has on the pressure side, suction side, leading edge, trailing edge, on the pressure side shock surface and suction side shock surface;
B. the platform cooling circuit in described platform, wherein said platform cooling circuit extends on the pressure side from the suction side of described platform; And
C. wherein said platform cooling circuit limits fluid flow path, and cooling medium is guided to plateau pressure side from platform suction side by described fluid flow path.
2. turbine bucket according to claim 1, is characterized in that, described platform cooling circuit is along on the pressure side reverses direction at least one times described in described platform.
3. turbine bucket according to claim 1, is characterized in that, described platform cooling circuit is along the described suction side reverses direction at least one times of described platform.
4. turbine bucket according to claim 1, is characterized in that, described turbine bucket also comprises at least one that be communicated with described platform cooling circuit fluid and exports.
5. turbine bucket according to claim 4, is characterized in that, at least one outlet described provides fluid to be communicated with by least one in described on the pressure side shock surface or described suction side shock surface.
6. turbine bucket according to claim 4, it is characterized in that, the top surface that described platform is also included in platform leading edge, extends between described on the pressure side shock surface and described suction side shock surface, at least one outlet described extends through the described top surface of described platform.
7. turbine bucket according to claim 1, it is characterized in that, described turbine bucket is also included in the vent pathway substantially extended abreast with described leading edge in described platform, and described vent pathway fluid is connected to the pressure-side portion of described platform cooling circuit.
8. turbine bucket according to claim 1, is characterized in that, described turbine bucket also comprises the aerofoil profile extended from described platform, and plateau pressure side and platform suction side separate by described aerofoil profile at least in part.
9. turbine bucket according to claim 8, is characterized in that, the described suction side of described platform cooling circuit from described platform below described aerofoil profile is walked on the pressure side described.
10. a turbine bucket, comprising:
A. main body, the main cooling circuit in main body described in described main part limitation;
B. at least in part around the platform of described main body, described platform has on the pressure side, suction side, leading edge, trailing edge, on the pressure side shock surface and suction side shock surface;
C. be located at the platform cooling circuit in described platform, described platform cooling circuit is communicated with the main cooling circuit fluid of described main body; And
D. wherein said platform cooling circuit in described platform from the described suction side of described platform a bit to extend to described in described platform on the pressure side along described trailing edge, described platform cooling circuit limits fluid flow path, and cooling medium is striden across platform trailing edge from the described main cooling circuit of described main body and guides to plateau pressure side by described fluid flow path.
11. turbine buckets according to claim 10, is characterized in that, described turbine bucket also comprises at least one that be communicated with described platform cooling circuit fluid and exports.
12. turbine buckets according to claim 11, is characterized in that, at least one outlet described extends through at least one in the described on the pressure side shock surface of described platform or described suction side shock surface.
13. turbine buckets according to claim 11, it is characterized in that, the top surface that described platform is also included in platform leading edge, extends between described on the pressure side shock surface and described suction side shock surface, at least one outlet described extends through the described top surface of described platform.
14. turbine buckets according to claim 10, is characterized in that, described platform cooling circuit is along on the pressure side reverses direction at least one times described in described platform.
15. turbine buckets according to claim 10, is characterized in that, described platform cooling circuit is along the described trailing edge reverses direction at least one times of described platform.
16. turbine buckets according to claim 10, is characterized in that, at least one outlet described comprises the first outlet and the second outlet.
17. turbine buckets according to claim 16, it is characterized in that, the top surface that described platform is also included in platform leading edge, extends between described on the pressure side shock surface and described suction side shock surface, described first exports at least one in the described on the pressure side shock surface or described suction side extending through described platform, and described second outlet extends through deck roof surface.
18. turbine buckets according to claim 10, is characterized in that, described platform cooling circuit extends across the described leading edge of described platform.
19. turbine buckets according to claim 10, it is characterized in that, described turbine bucket also comprises the aerofoil profile extended from described platform, plateau pressure side and platform suction side separate by described aerofoil profile at least in part, and the described suction side of described platform cooling circuit from described platform below described aerofoil profile is walked on the pressure side described.
20. 1 kinds of combustion gas turbines, comprising:
A. compressor, the burner in described compressor downstream and the turbo machine in described burner downstream, described turbo machine has at least one turbine bucket;
B. at least in part around the platform of described turbine bucket, described platform has leading edge, trailing edge, on the pressure side shock surface, suction side shock surface and top surface, described top surface has on the pressure side and suction side, and described platform limits one or more outlets of at least one extended through in the described on the pressure side shock surface of described platform, described suction side shock surface or described top surface;
C. the platform cooling circuit in described platform, described platform cooling circuit is communicated with at least one outlet fluid, and wherein said platform cooling circuit a bit to extend to described in described platform on the pressure side along described trailing edge from substantially adjacent with described suction side shock surface below the described top surface of described platform; And
D. wherein said platform cooling circuit limits fluid flow path, and cooling medium is guided to plateau pressure side from platform suction side and discharges described cooling medium by least one outlet described by described fluid flow path.
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US13/646,023 US20140096538A1 (en) | 2012-10-05 | 2012-10-05 | Platform cooling of a turbine blade assembly |
| US13/646023 | 2012-10-05 | ||
| PCT/US2013/063359 WO2014055811A1 (en) | 2012-10-05 | 2013-10-04 | Turbine blades with platform cooling and corresponding gas turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104704202A true CN104704202A (en) | 2015-06-10 |
Family
ID=49448300
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201380051904.0A Pending CN104704202A (en) | 2012-10-05 | 2013-10-04 | Turbine blades with platform cooling and corresponding gas turbine |
Country Status (5)
| Country | Link |
|---|---|
| US (1) | US20140096538A1 (en) |
| EP (1) | EP2912273A1 (en) |
| JP (1) | JP2015531451A (en) |
| CN (1) | CN104704202A (en) |
| WO (1) | WO2014055811A1 (en) |
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| US10053989B2 (en) | 2015-12-21 | 2018-08-21 | General Electric Company | Cooling circuit for a multi-wall blade |
| US9926788B2 (en) | 2015-12-21 | 2018-03-27 | General Electric Company | Cooling circuit for a multi-wall blade |
| US10060269B2 (en) | 2015-12-21 | 2018-08-28 | General Electric Company | Cooling circuits for a multi-wall blade |
| US9932838B2 (en) | 2015-12-21 | 2018-04-03 | General Electric Company | Cooling circuit for a multi-wall blade |
| US10119405B2 (en) | 2015-12-21 | 2018-11-06 | General Electric Company | Cooling circuit for a multi-wall blade |
| US10030526B2 (en) * | 2015-12-21 | 2018-07-24 | General Electric Company | Platform core feed for a multi-wall blade |
| US9976425B2 (en) | 2015-12-21 | 2018-05-22 | General Electric Company | Cooling circuit for a multi-wall blade |
| US10208607B2 (en) | 2016-08-18 | 2019-02-19 | General Electric Company | Cooling circuit for a multi-wall blade |
| US10221696B2 (en) | 2016-08-18 | 2019-03-05 | General Electric Company | Cooling circuit for a multi-wall blade |
| US10267162B2 (en) | 2016-08-18 | 2019-04-23 | General Electric Company | Platform core feed for a multi-wall blade |
| US10208608B2 (en) | 2016-08-18 | 2019-02-19 | General Electric Company | Cooling circuit for a multi-wall blade |
| US10227877B2 (en) | 2016-08-18 | 2019-03-12 | General Electric Company | Cooling circuit for a multi-wall blade |
| US20190085706A1 (en) * | 2017-09-18 | 2019-03-21 | General Electric Company | Turbine engine airfoil assembly |
| US10787932B2 (en) * | 2018-07-13 | 2020-09-29 | Honeywell International Inc. | Turbine blade with dust tolerant cooling system |
| DE102019108811B4 (en) | 2019-04-04 | 2024-02-29 | Man Energy Solutions Se | Rotor blade of a turbomachine |
| US20240011398A1 (en) * | 2022-05-02 | 2024-01-11 | Siemens Energy Global GmbH & Co. KG | Turbine component having platform cooling circuit |
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- 2013-10-04 JP JP2015535796A patent/JP2015531451A/en active Pending
- 2013-10-04 EP EP13780004.1A patent/EP2912273A1/en not_active Withdrawn
- 2013-10-04 WO PCT/US2013/063359 patent/WO2014055811A1/en active Application Filing
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| US6017189A (en) * | 1997-01-30 | 2000-01-25 | Societe National D'etede Et De Construction De Moteurs D'aviation (S.N.E.C.M.A.) | Cooling system for turbine blade platforms |
| US5848876A (en) * | 1997-02-11 | 1998-12-15 | Mitsubishi Heavy Industries, Ltd. | Cooling system for cooling platform of gas turbine moving blade |
| DE19713268A1 (en) * | 1997-03-29 | 1998-10-01 | Asea Brown Boveri | Solid turbine blade cooling system |
| EP1052375A2 (en) * | 1999-05-14 | 2000-11-15 | General Electric Company | Apparatus and method for relieving thermally induced stresses in inner and outer bands of thermally cooled turbine nozzle stages |
| US20070116574A1 (en) * | 2005-11-21 | 2007-05-24 | General Electric Company | Gas turbine bucket with cooled platform leading edge and method of cooling platform leading edge |
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Also Published As
| Publication number | Publication date |
|---|---|
| US20140096538A1 (en) | 2014-04-10 |
| WO2014055811A1 (en) | 2014-04-10 |
| JP2015531451A (en) | 2015-11-02 |
| EP2912273A1 (en) | 2015-09-02 |
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