CN105705266A - Ceramic casting core having an integral vane internal core and shroud backside shell for vane segment casting - Google Patents
Ceramic casting core having an integral vane internal core and shroud backside shell for vane segment casting Download PDFInfo
- Publication number
- CN105705266A CN105705266A CN201480061191.0A CN201480061191A CN105705266A CN 105705266 A CN105705266 A CN 105705266A CN 201480061191 A CN201480061191 A CN 201480061191A CN 105705266 A CN105705266 A CN 105705266A
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- CN
- China
- Prior art keywords
- core
- shell
- shaped
- back surface
- ceramic core
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22C—FOUNDRY MOULDING
- B22C9/00—Moulds or cores; Moulding processes
- B22C9/22—Moulds for peculiarly-shaped castings
- B22C9/24—Moulds for peculiarly-shaped castings for hollow articles
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22C—FOUNDRY MOULDING
- B22C7/00—Patterns; Manufacture thereof so far as not provided for in other classes
- B22C7/06—Core boxes
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22C—FOUNDRY MOULDING
- B22C9/00—Moulds or cores; Moulding processes
- B22C9/02—Sand moulds or like moulds for shaped castings
- B22C9/04—Use of lost patterns
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22C—FOUNDRY MOULDING
- B22C9/00—Moulds or cores; Moulding processes
- B22C9/10—Cores; Manufacture or installation of cores
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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
- F01D5/188—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall
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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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
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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
- F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Molds, Cores, And Manufacturing Methods Thereof (AREA)
Abstract
A cast ceramic core (110), including: an airfoil portion (116) shaped to define an inner surface (56) of an airfoil (52) of a vane segment (50); and a shell portion (122) having a backside-shaping surface (120) shaped to define a backside surface (68) of a shroud (62) of the vane segment. The backside-shaping surface has a higher elevation (132) and a lower elevation (134). The higher elevation is set apart from a nearest point (138) on the airfoil portion by the lower elevation. The airfoil portion and the shell portion are cast as a monolithic body during a single casting pour.
Description
Technical field
Invention relates to the casting of the cooled fin section used in gas-turbine unit。Specifically, invention relates to the ceramic casting core plus the shroud external shell part of the back surface of the shroud for forming fin section of the traditional core segment with the internal cooling channel in the aerofoil profile for forming fin section。
Background technology
Industrial gas turbine engine includes for compressed-air actuated compressor, for the burner apparatus making fuel and compressed-air actuated mixture burn with for extracting the turbine of energy from burning gases。Turbine portion includes the rows of blade being fixed to armature spindle, and all blades therein are all rotated by burning gases in Energy extraction process。Is the rows of fixed tab being properly oriented by burning gases when burning gases are advanced in turbine between rows of turbine blade。Each row's fin includes fin section, and each section has interior shroud and the peripheral band of the end opposite being fixed at least one aerofoil profile。In a lot of turbines, aerofoil profile can also be cooled by cooled via internal cooling channel and shroud dorsal part。These cooled aerofoil profiles can be a part for first and the even turbine blade of second row。Cooling can include the convection current cooling relying on cooling air flowing on surface to be cooled, and/or by being placed in the internal cooling channel of aerofoil profile and the impinging cooling of the shock plate plug-in unit of the dorsal part of adjacent shroud。
Aerofoil profile and shroud can by together with casting be consequently formed monolithic fin section。Alternately, aerofoil profile and shroud can be cast and then welded together individually。The inner passage of aerofoil profile requires that the use of ceramic core is to create passage and to limit interior surface configuration during casting technique。Those ceramic cases typically formed by the wax-pattern (waxpattern) around fin section at interior remaining part including inside and outside shroud of tab area section surface limit, and wherein wax-pattern is formed around ceramic core。Wax-pattern is then removed, and leaves a void in the shape of fin section, and wherein ceramic core limits the surface of the inner passage of aerofoil profile and the remaining part on the surface of ceramic case restriction fin section。
Little be characterized by some of the surface of fin section desired, including the back surface of the inner passage of aerofoil profile and shroud, because they can be used in combination with improving impinging cooling with impact jet flow。Little feature can be readily formed at by ceramic core in the surface of inner passage of aerofoil profile, because the little feature on ceramic core is survived in the step lead to final casting, and is directly printed on final fin section。But the little feature in the back surface of shroud will be formed by wax-pattern, because wax-pattern limits the back surface of shroud。Wax-pattern is soft material。For this reason, if little feature is printed on the surface of wax-pattern and is then subjected to impregnation technology, form ceramic case during this period, then little feature is twisted and/or loses。Because the little feature in wax-pattern can not be survived in impregnation technology, so when little feature will produce in time being exposed to the wax-pattern of impregnation technology, being limited the surface of (and then being limited by wax-pattern) by shell and can not have little feature of fin section。
The technology being used for overcoming this problem is the discrete ceramic plug-in unit using the individually casting little feature to be formed in shroud back surface。Wax-pattern becomes around the hull shape of ceramic core with ceramic insert and removal, leaves the space for fin section。Ceramic core limits the interior surface of aerofoil profile and little feature thereof in the method, and ceramic insert limits shroud back surface and little feature thereof, and the remaining part of tab area section surface is become by hull shape。But, when using ceramic insert, the position of ceramic insert is difficult to accurately control and the quality of foundry goods is less than acceptable。Have the space of improvement in this area for previous reasons。
Accompanying drawing explanation
In the following description in view of accompanying drawing illustrates invention, accompanying drawing illustrates:
Fig. 1 is the schematic cross-sectional of prior art fin section foundry goods。
Fig. 2 is the schematic cross-sectional of the fin section using casting core disclosed herein and method。
The schematic cross-sectional of prior art ceramic core when Fig. 3 is to cast in prior art core mold。
Fig. 4 is the schematic cross-sectional of the integrally casting core with airfoil section and shroud shell part during casting in the core mold with flexible type core mold back boxing。
Fig. 4 A is the feature of the details of Fig. 4。
Fig. 5 is the schematic cross-sectional of the prior art ceramic core of Fig. 3。
Fig. 6 is the schematic cross-sectional of the integrally casting core of Fig. 4。
Fig. 7 is the prior art ceramic core schematic cross-sectional with the prior art wax-pattern using assembly to be formed of the Fig. 5 being positioned in prior art wax die inside。
Fig. 8 is the integrally casting core schematic cross-sectional with the wax-pattern using assembly to be formed of the Fig. 6 being positioned in wax die inside disclosed herein。
Fig. 9 is the schematic cross-sectional of the prior art ceramic core of Fig. 7 and prior art ceramic die。
Figure 10 is the schematic cross-sectional of the integrally casting core of Fig. 8 and wax-pattern。
Figure 11 is the prior art ceramic core of Fig. 9 and prior art ceramic die and the schematic cross-sectional of prior art ceramic case formed around assembly。
Figure 12 is the ceramic core of Figure 10 and wax-pattern and the schematic cross-sectional of ceramic case formed around assembly。
Figure 13 is the schematic cross-sectional of the prior art ceramic core of the Figure 11 with the space for prior art fin section and prior art ceramic case。
Figure 14 is the schematic cross-sectional of the integrally casting core of the Figure 12 with the space for fin section and ceramic case。
Figure 15 is the prior art ceramic core of Figure 11 and prior art ceramic case and the schematic cross-sectional of prior art fin section cast wherein。
Figure 16 is the integrally casting core of Figure 14 and ceramic case and the schematic cross-sectional of fin section cast wherein。
Detailed description of the invention
The present inventor has invented method and the integrally casting core of a kind of uniqueness, by them, when airfoil section and the neckband (or multiple part) of fin section can form fine-feature when being cast to be formed monolithic, cooled casting fin section on the dorsal part of the shroud of cooled fin section simultaneously。Fine-feature can be able to be used in combination with more effectively cooling down the heat transfer characteristics of shroud dorsal part with impinging cooling jet。The method and casting core can be achieved by the use of flexible type core mold back boxing in certain embodiments。Flexible back boxing makes it possible to feature and is merged in the surface of foundry goods, and this is impossible when using rigid core for building mould。This is because rigid core for building mould must by along pulling plane (pullplane) separately。When mould must be opened when sliding along the surface of foundry goods, two surfaces can not be formed such that they are interfered with this slip。Owing to the very multipart geometry of such as fin section etc., which has limited fine-feature and can form the plane at place, such as shroud back surface in foundry goods。Flexible back boxing at rigid core for building die inside avoids this problem, because flexible back boxing is used to form fine-feature and flexible back boxing can bend around fine-feature when being removed。
Inventor make use of the advantage of this flexibility back boxing to create integrally casting core, it innovatively forms the cooling duct of airfoil section of fin section and has concurrently formed the back surface of shroud, this back surface former by ceramic case or discrete ceramic insert formed。Fine-feature can also use integrally casting core to be formed in back surface, because in this casting method, and shroud dorsal part to be therefore any shroud back surface feature be formed directly in fin section by integrally core during casting。Owing to one core forms fine-feature, so not about out-of-alignment worry when losing or formed by discrete ceramic insert of fine-feature when being formed by wax-pattern。Owing to flexible back boxing can be pulled out from round little feature, wherein this little feature can stop the separation of rigid core for building mould back boxing, so the worry not separated about core mold。
Fig. 1 is the schematic cross-sectional of the prior art fin section 10 with the aerofoil profile 12 having aerofoil profile inner passage 14, airfoil inner surface 16 and aerofoil profile outer surface 18。Interior shroud 20 and peripheral band 22 are disposed in the inner 24 and outer end 26 place of aerofoil profile 12。Shroud respectively has smooth, namely to lack fine heat transfer characteristics corresponding back surface 28。Aerofoil profile is impacted plug-in unit 30 and be can be used to form the impact jet flow for making airfoil inner surface cool down。Shroud shock plate 32 can be used to form the impact jet flow for making shroud back surface 28 cool down。
Fig. 2 is the schematic cross-sectional of the high temperature alloy fin section 50 using teachings herein to be formed。Fin section 50 includes the aerofoil profile 52 with aerofoil profile inner passage 54, airfoil inner surface 56 and aerofoil profile outer surface 58。Interior shroud 60 and peripheral band 62 are disposed in the inner 64 and outer end 66 place of aerofoil profile 52。Shroud respectively has corresponding back surface 68。Little feature 70 can be formed in airfoil inner surface 56 and/or in shroud back surface 68 or both in。These little features 70 can be configured to the heat transfer characteristics worked together with impacting the impact jet flow of plug-in unit 30 and/or shroud shock plate 32 formation by aerofoil profile。These little features 70 can be taked for improving the heat known any shape of transmission, including the array of repetition geometry of the array etc. of such as pit。Alternately, it is possible to by for heat transmission being made to maximize by the various different sizes of the little feature 70 of local cutting and shape when necessary。
The fin section casting technique of prior art and the core that is associated and technique disclosed herein and the core that is associated schematically are compared by Fig. 3 to Figure 16。Fig. 3 schematically depict the formation of the prior art ceramic casting core 100 in prior art rigid core for building mould 102。Fig. 4 is the schematic cross-sectional of the integrally casting core 110 using flexible back boxing 112 to be formed with the rigid core for building mould 114 being associated。Integrally casting core 110 includes the core airfoil section 116 limiting aerofoil profile inner passage 54 and the shell part 118 (housing portion) from core airfoil section 116 horizontal expansion and the core shroud dorsal part profiled surface 120 with the back surface 68 limiting peripheral band 62。Integrally casting core 110 can also include the relative shell part 122 (inner shell sections) from core airfoil section 116 horizontal expansion and the relative core shroud dorsal part profiled surface 124 with the back surface 68 limiting interior shroud 60。Core neckband 118,122 can have the core shell feature 130 being configured to be formed little feature 70。Core airfoil section 116 can have the core aerofoil profile feature 140 being configured to be formed little feature 70 on airfoil inner surface 56。Core shell feature 130 can include high height 132 and be adjacent to the lower height 134 of high height 132, and its camber is relative to corresponding core neckband 118。
Due to the geometry of integrally casting core 110, if employing rigid core for building mould, then rigid core for building mould will need by along line 136 separately。But, when layout type core shell feature 130 as shown in the figure, the interference between the inverse features in core shell feature 130 and rigid core for building mould wherein has lower height 134 between the closest approach 138 on the surface 142 of high height 132 and core airfoil section 116, so will stop the transverse shifting between core neckband 118 and rigid core for building mould。This must will stop the movement along line 136。But, flexible back boxing is sufficiently flexible it to be removed without they are caused any harm from round core shell feature 130。Cause the separation stoping rigid core for building mould in like fashion interfere but can be with any pattern in the core shroud dorsal part profiled surface 120 that flexible back boxing 112 is formed it is contemplated that。One such example can be pit or the array of groove or stumble band etc. unjustified with line 136。
Fig. 5 is the schematic cross-sectional of the prior art ceramic casting core 100 of the Fig. 3 under the state that prior art rigid core for building mould 102 is removed。Prior art ceramic casting core is removed as green and can be sintered at this moment。Fig. 6 is the schematic cross-sectional of flexible back boxing 112 and the integrally casting core 110 under the removed state of rigid core for building mould 114 being associated。Equally, integrally casting core 110 is removed as green and can be sintered at this moment。
Fig. 7 is positioned at the schematic cross-sectional of the prior art ceramic casting core 100 of the Fig. 5 inside prior art wax-pattern tool 150, has been formed with prior art wax-pattern 152 between which。Prior art wax-pattern 152 is in the shape of prior art fin section 10 to be formed。Owing to the geometry to be formed of fin section 50, the geometry of prior art wax-pattern tool 150 includes entering the projection 154 in prior art wax-pattern 152。This projection 154 be prior art wax-pattern tool 150 make its be more difficult to remove complicated point。
Fig. 8 is the schematic cross-sectional of the integrally casting core 110 of the Fig. 6 inside wax-pattern tool 160, has been formed with wax-pattern 162 between which。Wax-pattern 162 is in the shape of fin section 50 to be formed。Owing to the difformity of integrally casting core 110, the projection 154 of prior art wax-pattern tool 150 is absent from。Result is the interior shape of wax-pattern tool 160 simply too much。The simplicity of this increase makes it is easier to remove wax-pattern tool 160, and thereby increases available process option。
The prior art ceramic casting core 100 of the Fig. 7 under the state that Fig. 9 is prior art wax-pattern tool 150 removal and the schematic cross-sectional of prior art wax-pattern tool 150。Similarly, the integrally casting core 110 of the Fig. 8 under the state that Figure 10 is wax-pattern tool 160 removal and the schematic cross-sectional of wax-pattern 162。Figure 11 is the schematic cross-sectional of the prior art ceramic casting core 100 at the Fig. 9 formed after the impregnation technology of prior art ceramic case 170 and prior art wax-pattern tool 150。Being similar to the projection 154 of prior art wax-pattern tool 150, prior art ceramic case 170 includes projection 172。Figure 12 is the schematic cross-sectional of the integrally casting core 110 at the Figure 10 formed after the impregnation technology of ceramic case 180 and wax-pattern 162。The projection 172 of prior art ceramic case 170 no longer exists。In those situations of quality surface relatively low compared with defining formed with integrally casting core 110 at ceramic case 180, eliminate projection 172 and reduce the amount formed by ceramic case 172 of fin section 50, and this represents the improvement to fin section 50。
The prior art ceramic casting core 100 of the Figure 11 under the state that Figure 13 is prior art wax-pattern 152 removal and the schematic cross-sectional of prior art ceramic case 170。Which leaves molten alloy and will be poured onto in it to form the prior art space 190 of prior art fin section 10 during single casting is toppled over。The integrally casting core 110 of the Figure 12 under the state that Figure 14 is wax-pattern 162 removal and the schematic cross-sectional of ceramic case 180。Which leaves molten alloy and will be poured onto in it during single casting to form the space 200 of monolithic integrally casting core 110。
Figure 15 is the schematic cross-sectional of the prior art ceramic casting core 100 of Figure 13 and prior art ceramic case 170 and the prior art fin section 10 that has been cast in prior art space 190。In the prior art full form casting process (lost wax casting), prior art ceramic case 170 forms all of outer surface 210 and the back surface 28 of shroud 20,22。Prior art ceramic casting core 100 is limited to form airfoil inner surface 16。
Figure 16 is the schematic cross-sectional of the integrally casting core 110 of Figure 14 and ceramic case 180 and the fin section 50 that has been casted in space 200。In method disclosed here, integrally casting core 100 not only forms airfoil inner surface 56 now, and forms the back surface 68 of shroud 60,62。Ceramic case 180 is limited to form outer surface 210 now。This change allows surface character 70 to be formed in the back surface 68 of shroud 60,62 by the identical casting forming aerofoil profile inner passage 54, and this cannot complete before。Surface character 70 will not image surface feature 70 be contingent when being formed in prior art ceramic case 170 by prior art wax-pattern 152 is washed off, and image surface feature 70 will not use that prior art ceramic insert is contingent when being formed reorientates。For this reason, surface character 70 can be done finer compared with being likely to up to now make。As a result, this represents the improvement on this area。
Although shown here and describe various embodiments of the present invention, but it is evident that such embodiment only provides by way of example。Many changes, change and replacement can be carried out without departing from invention here。It is therefore intended that invention is only limited by the spirit and scope of appended claims。
Claims (16)
1. a castable ceramic core, including:
Airfoil section, is shaped as the inner surface of the aerofoil profile limiting fin section；With
Shell part, dorsal part profiled surface including the back surface being shaped as the shroud limiting described fin section, described dorsal part profiled surface includes high height and lower height, and described high height is set to be separated with the closest approach on described airfoil section by described lower height
Wherein said airfoil section and described shell part are cast the single block toppling over period as single casting。
2. castable ceramic core according to claim 1, the described back surface of the peripheral band of the partially defined described fin section of wherein said shell, and wherein said castable ceramic core farther includes relative shell part, described relative shell part includes the relative dorsal part profiled surface being shaped as the back surface of the interior shroud limiting described fin section, described relative dorsal part profiled surface includes described high height and described lower height, and described high height is set to be separated with the corresponding closest approach of described airfoil section by described lower height。
3. a castable ceramic core, including being shaped as the airfoil section of inner surface of the aerofoil profile limiting fin section and being shaped as the shell part of back surface of the shroud limiting described fin section, wherein said airfoil section and described shell part are formed as unit casting。
4. castable ceramic core according to claim 3, wherein said shell part farther includes the core shell feature of the heat transfer characteristics being shaped as in the described back surface limiting fin section shroud。
5. castable ceramic core according to claim 4, wherein said airfoil section includes the core aerofoil profile feature of the heat transfer characteristics being shaped as on the described inner surface limiting fin section aerofoil profile。
6. castable ceramic core according to claim 4, wherein said core shell feature forms high height and lower height in described shell part, and described high height is set to separate with the closest approach on described airfoil section。
7. castable ceramic core according to claim 3, the described back surface of the peripheral band of the partially defined described fin section of wherein said shell, and wherein said castable ceramic core farther includes to be shaped as the relative shell part of the back surface of the interior shroud limiting described fin section。
8. castable ceramic core according to claim 7, wherein said shell part farther includes the core shell feature of the heat transfer characteristics being shaped as in the described back surface limiting described peripheral band, and wherein said relative shell part farther includes the core shell feature of the heat transfer characteristics being shaped as in the described back surface limiting described interior shroud。
9. castable ceramic core according to claim 8, wherein the described core shell feature at least one in described shell part forms high height and lower height at least one shell part described, and described high height is set to separate with the closest approach on described airfoil section。
10. castable ceramic core according to claim 8, wherein the described core shell feature in two shell parts includes multiple pit。
11. a castable ceramic core, including:
Single block, including:
Airfoil section, is shaped as the inner surface of the aerofoil profile limiting fin section；
Housing portion, is shaped as the back surface of the peripheral band limiting described fin section；With
Inner shell sections, including the core dorsal part profiled surface of the back surface being shaped as the interior shroud limiting described fin section。
12. castable ceramic core according to claim 11, at least one in wherein said core shell part is further shaped the heat transfer characteristics in the corresponding back surface for limiting described fin section。
13. castable ceramic core according to claim 12, wherein said being formed in further at least one shell part described forms high height and lower height, and described high height is set to separate with the closest approach on described airfoil section。
14. castable ceramic core according to claim 12, wherein said it be formed in corresponding back surface further and form multiple pit。
15. castable ceramic core according to claim 12, two of which dorsal part profiled surface is further shaped the heat transfer characteristics in the corresponding back surface for limiting described fin section, described being formed in each dorsal part profiled surface further and form lower height and lower height, the corresponding closest approach that described high height is set to described airfoil section is separated。
16. castable ceramic core according to claim 15, wherein said further shaping forms multiple pits。
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US13/998,541 US20150122450A1 (en) | 2013-11-07 | 2013-11-07 | Ceramic casting core having an integral vane internal core and shroud backside shell for vane segment casting |
| US13/998,541 | 2013-11-07 | ||
| PCT/US2014/062606 WO2015069495A1 (en) | 2013-11-07 | 2014-10-28 | Ceramic casting core having an integral vane internal core and shroud backside shell for vane segment casting |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105705266A true CN105705266A (en) | 2016-06-22 |
Family
ID=51868361
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201480061191.0A Pending CN105705266A (en) | 2013-11-07 | 2014-10-28 | Ceramic casting core having an integral vane internal core and shroud backside shell for vane segment casting |
Country Status (5)
| Country | Link |
|---|---|
| US (1) | US20150122450A1 (en) |
| EP (1) | EP3065897A1 (en) |
| JP (1) | JP2016539274A (en) |
| CN (1) | CN105705266A (en) |
| WO (1) | WO2015069495A1 (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108778561B (en) * | 2016-03-18 | 2021-01-05 | 西门子股份公司 | Tool for ceramic cores and method of manufacture |
| US10822987B1 (en) | 2019-04-16 | 2020-11-03 | Pratt & Whitney Canada Corp. | Turbine stator outer shroud cooling fins |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5201847A (en) * | 1991-11-21 | 1993-04-13 | Westinghouse Electric Corp. | Shroud design |
| EP1043479A2 (en) * | 1999-04-06 | 2000-10-11 | General Electric Company | Internally grooved turbine wall |
| CN1693014A (en) * | 2004-05-06 | 2005-11-09 | 通用电气公司 | Method and apparatus for determining the location of core-generated features in an investment casting |
| WO2009121716A1 (en) * | 2008-03-31 | 2009-10-08 | Alstom Technology Ltd | Blade for a gas turbine |
| EP2471612A1 (en) * | 2010-12-30 | 2012-07-04 | United Technologies Corporation | Method and casting core for forming a landing for welding a baffle inserted into an airfoil |
| FR2987292A1 (en) * | 2012-02-28 | 2013-08-30 | Snecma | Casting core used to manufacture stator sector of gas turbine of aircraft, comprises core comprising set of blades for formation of internal cavities in each paddle of sector and blades maintenance element to connect blades between paddles |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5662160A (en) * | 1995-10-12 | 1997-09-02 | General Electric Co. | Turbine nozzle and related casting method for optimal fillet wall thickness control |
| US6502622B2 (en) * | 2001-05-24 | 2003-01-07 | General Electric Company | Casting having an enhanced heat transfer, surface, and mold and pattern for forming same |
| US20110132564A1 (en) * | 2009-12-08 | 2011-06-09 | Merrill Gary B | Investment casting utilizing flexible wax pattern tool |
| EP2397653A1 (en) * | 2010-06-17 | 2011-12-21 | Siemens Aktiengesellschaft | Platform segment for supporting a nozzle guide vane for a gas turbine and method of cooling thereof |
-
2013
- 2013-11-07 US US13/998,541 patent/US20150122450A1/en not_active Abandoned
-
2014
- 2014-10-28 EP EP14795762.5A patent/EP3065897A1/en not_active Withdrawn
- 2014-10-28 WO PCT/US2014/062606 patent/WO2015069495A1/en active Application Filing
- 2014-10-28 JP JP2016528047A patent/JP2016539274A/en not_active Ceased
- 2014-10-28 CN CN201480061191.0A patent/CN105705266A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5201847A (en) * | 1991-11-21 | 1993-04-13 | Westinghouse Electric Corp. | Shroud design |
| EP1043479A2 (en) * | 1999-04-06 | 2000-10-11 | General Electric Company | Internally grooved turbine wall |
| CN1693014A (en) * | 2004-05-06 | 2005-11-09 | 通用电气公司 | Method and apparatus for determining the location of core-generated features in an investment casting |
| WO2009121716A1 (en) * | 2008-03-31 | 2009-10-08 | Alstom Technology Ltd | Blade for a gas turbine |
| EP2471612A1 (en) * | 2010-12-30 | 2012-07-04 | United Technologies Corporation | Method and casting core for forming a landing for welding a baffle inserted into an airfoil |
| FR2987292A1 (en) * | 2012-02-28 | 2013-08-30 | Snecma | Casting core used to manufacture stator sector of gas turbine of aircraft, comprises core comprising set of blades for formation of internal cavities in each paddle of sector and blades maintenance element to connect blades between paddles |
Also Published As
| Publication number | Publication date |
|---|---|
| EP3065897A1 (en) | 2016-09-14 |
| WO2015069495A1 (en) | 2015-05-14 |
| US20150122450A1 (en) | 2015-05-07 |
| JP2016539274A (en) | 2016-12-15 |
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Application publication date: 20160622 |