EP2265800A1 - Kühlkanalanordnung innerhalb eines hohlgegossenen gussteils - Google Patents
Kühlkanalanordnung innerhalb eines hohlgegossenen gussteilsInfo
- Publication number
- EP2265800A1 EP2265800A1 EP09727227A EP09727227A EP2265800A1 EP 2265800 A1 EP2265800 A1 EP 2265800A1 EP 09727227 A EP09727227 A EP 09727227A EP 09727227 A EP09727227 A EP 09727227A EP 2265800 A1 EP2265800 A1 EP 2265800A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- cooling
- contour
- arrangement according
- along
- casting
- 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.)
- Granted
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- 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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/20—Manufacture essentially without removing material
- F05D2230/21—Manufacture essentially without removing material by casting
-
- 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
- F05D2240/10—Stators
- F05D2240/12—Fluid guiding means, e.g. vanes
- F05D2240/122—Fluid guiding means, e.g. vanes related to the trailing edge of a stator vane
-
- 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
- F05D2240/20—Rotors
- F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
- F05D2240/304—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the trailing edge of a rotor blade
-
- 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
- F05D2260/221—Improvement of heat transfer
- F05D2260/2214—Improvement of heat transfer by increasing the heat transfer surface
- F05D2260/22141—Improvement of heat transfer by increasing the heat transfer surface using fins or ribs
Definitions
- the invention relates to a cooling channel arrangement within a hollow casted casting, with a flow area for a coolant delimited by at least two spaced-apart casting walls, which is divided into two cooling channels in the flow direction of at least one ribbed train connected to both casting walls.
- Hollow-cast parts with intimately provided cooling channel arrangements relate to the purposes of the invention primarily in gas and steam turbine to be integrated components that are operationally exposed to high process temperatures and require effective cooling to avoid thermally induced material degradation.
- Such castings in particular represent guide vanes and rotor blades within turbine stages, which are directly exposed to the hot gases of a gas turbine process.
- the cooling of such blading takes place by means of cooling air, which is branched off on the compressor side and fed via openings within the respective blade roots into the airfoils which have cavities for cooling purposes.
- FIGS. 2 a and b show a guide vane known per se, with a vane platform 1 and a vane cover 2, between which the vane leaf 3 with a vane leading edge 4 and a vane trailing edge 5 extends.
- cooling air K reaches both through opening
- For effective cooling of the vane blade 3 are located in the interior of the guide vane flow contours, which ensure the most intimate possible thermal contact between the supplied cooling air and to be cooled inside the vane wall. Particularly in the flow region immediately upstream of the trailing edge 5, which is shown enlarged in FIG.
- lost cores are required for the casting process, in which the negative contours of all structures to be provided within the casting, in particular the flow contours affecting the cooling air flow, are to be incorporated.
- the rip creases 6 shown in the detail illustration according to FIG. 2 and the pin-like pins 8 therebetween, which are shown again in FIG. 3 a in a top view for better illustration it is necessary to provide a casting core 9 which likewise is shown in FIG Top view is shown, which must provide for the production of the individual rib trains via groove-like recesses 10 and for generating the pin-like pins 8 corresponding through holes 1 1.
- the invention has for its object, a cooling arrangement within a hollow cast casting, with one of at least two spaced apart casting walls delimiting flow area for a coolant, which is divided in the flow direction of at least one connected to two casting walls Rippenzug in two cooling channels, such on the one hand the measures taken to stabilize the casting core required for the production of the casting should remain largely unaffected, but the cooling effect of passing through the cooling channel arrangement coolant should be significantly improved.
- a cooling arrangement within a hollow cast casting with one of at least two spaced apart casting walls delimiting flow area for a coolant, which is divided in the flow direction of at least one connected to two casting walls Rippenzug in two cooling channels, such on the one hand the measures taken to stabilize the casting core required for the production of the casting should remain largely unaffected, but the cooling effect of passing through the cooling channel arrangement coolant should be significantly improved.
- a cooling arrangement within a hollow cast part is formed such that at least one interruption is provided along the at least one rib train, at which two rib ends are spaced apart, of which one rib end forms a contour in the manner of a " With the aid of such a flow contour it is possible, as the further explanations will show, to largely or completely prevent coolant flow through the interruption along a rib train.
- the solution according to the measure only requires an additional contour along the Rippenzuges in the region of an interruption, by the stability of a casting core is not affected by any means. Even with the measure according to the solution, it is possible to provide connection areas between the cooling passages separated by the rib trains in order to realize in this way a self-contained and mechanically stable casting core.
- 3a, b, c illustrate the formation of a casting core to create cooling channels with ribbed and pin-like pins
- FIG. 1a shows the region of an interruption 13 along a rib train 6, wherein two rib ends 61, 62 are arranged at a distance from one another along the rib train 6.
- a coolant flow K rests along the rib train 6 in the direction of flow indicated by the arrows.
- the rib end 61 which is provided upstream of the interruption 13, in this case according to the solution has a contour 14 in the manner of a dog bone, whereby the coolant flow K does not pass through the interruptions 13 as in the illustrated case study in Figure 4b in the context of cross flows K ' , but respectively on both sides of the interruption 13 along the respective cooling channel 7 flows past.
- the contour 14 formed on the rib end 61 in the manner of a dog bone has an extension D oriented transversely to the rib longitudinal extension which corresponds at least to 1.5 times the respective rib width d.
- the dog-bone-shaped rib end contour 14 is optimized under flow dynamic aspects and has a round and thus a flow resistance reducing surface contour. The axial distance between the two along the interruption The length of the lateral extension D of the dog-bone-shaped contour 14 should not exceed three times the length of the ribs 61, 62 facing each other.
- FIG. 1 b A graphic simulation result is shown in FIG. 1 b.
- the dark line regions indicate the presence of coolant and it is assumed that the flow region shown in Figure 1 b is traversed by coolant K from left to right. Due to the dog-bone-shaped rib end contour 14, which is provided upstream of the interruption 13, it is demonstrably possible to reduce to a minimum those flow portions which pass through the interruption 13 from a cooling channel 7 into the adjacent cooling channel. In this way, it is possible to ensure the cooling efficiency of the coolant K within a cooling passage 7, despite the provision of design-related interruptions 13.
- the dog-bone-like contours 14 are respectively provided at the upstream rib end for each individual interruption 13.
- the dog bone contour 14 is provided at the downstream end for each discrete interruption 13 along the ribcuff.
- the dogbone contours 14 are again uniformly located at the upstream rib end at the location of each break 13.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CH4712008 | 2008-03-31 | ||
PCT/EP2009/053108 WO2009121715A1 (de) | 2008-03-31 | 2009-03-17 | Kühlkanalanordnung innerhalb eines hohlgegossenen gussteils |
Publications (2)
Publication Number | Publication Date |
---|---|
EP2265800A1 true EP2265800A1 (de) | 2010-12-29 |
EP2265800B1 EP2265800B1 (de) | 2017-11-01 |
Family
ID=39689142
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP09727227.2A Not-in-force EP2265800B1 (de) | 2008-03-31 | 2009-03-17 | Kühlkanalanordnung innerhalb eines hohlgegossenen gussteils |
Country Status (3)
Country | Link |
---|---|
US (1) | US8360725B2 (de) |
EP (1) | EP2265800B1 (de) |
WO (1) | WO2009121715A1 (de) |
Families Citing this family (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US9810071B2 (en) * | 2013-09-27 | 2017-11-07 | Pratt & Whitney Canada Corp. | Internally cooled airfoil |
EP3063388B1 (de) * | 2013-10-29 | 2019-01-02 | United Technologies Corporation | Sockel mit wärmetransferverstärker |
DE102015203175A1 (de) * | 2015-02-23 | 2016-08-25 | Siemens Aktiengesellschaft | Leit- oder Laufschaufeleinrichtung und Gießkern |
US10641174B2 (en) | 2017-01-18 | 2020-05-05 | General Electric Company | Rotor shaft cooling |
EP3421721A1 (de) * | 2017-06-28 | 2019-01-02 | Siemens Aktiengesellschaft | Turbomaschinenkomponente und verfahren zur herstellung einer turbomaschinenkomponente |
EP3425772B1 (de) | 2017-07-03 | 2020-11-25 | GE Energy Power Conversion Technology Limited | Elektrisch umlaufende maschine, die einen stator und einen rotor umfasst |
US10830072B2 (en) * | 2017-07-24 | 2020-11-10 | General Electric Company | Turbomachine airfoil |
US20200149401A1 (en) * | 2018-11-09 | 2020-05-14 | United Technologies Corporation | Airfoil with arced baffle |
US10975710B2 (en) * | 2018-12-05 | 2021-04-13 | Raytheon Technologies Corporation | Cooling circuit for gas turbine engine component |
Family Cites Families (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5536143A (en) * | 1995-03-31 | 1996-07-16 | General Electric Co. | Closed circuit steam cooled bucket |
US5772397A (en) * | 1996-05-08 | 1998-06-30 | Alliedsignal Inc. | Gas turbine airfoil with aft internal cooling |
US6213714B1 (en) * | 1999-06-29 | 2001-04-10 | Allison Advanced Development Company | Cooled airfoil |
US6234754B1 (en) * | 1999-08-09 | 2001-05-22 | United Technologies Corporation | Coolable airfoil structure |
US6254334B1 (en) * | 1999-10-05 | 2001-07-03 | United Technologies Corporation | Method and apparatus for cooling a wall within a gas turbine engine |
US6402470B1 (en) * | 1999-10-05 | 2002-06-11 | United Technologies Corporation | Method and apparatus for cooling a wall within a gas turbine engine |
US6602047B1 (en) * | 2002-02-28 | 2003-08-05 | General Electric Company | Methods and apparatus for cooling gas turbine nozzles |
US6902372B2 (en) * | 2003-09-04 | 2005-06-07 | Siemens Westinghouse Power Corporation | Cooling system for a turbine blade |
US7186084B2 (en) * | 2003-11-19 | 2007-03-06 | General Electric Company | Hot gas path component with mesh and dimpled cooling |
US7600966B2 (en) * | 2006-01-17 | 2009-10-13 | United Technologies Corporation | Turbine airfoil with improved cooling |
-
2009
- 2009-03-17 WO PCT/EP2009/053108 patent/WO2009121715A1/de active Application Filing
- 2009-03-17 EP EP09727227.2A patent/EP2265800B1/de not_active Not-in-force
-
2010
- 2010-09-29 US US12/893,307 patent/US8360725B2/en not_active Expired - Fee Related
Non-Patent Citations (2)
Title |
---|
None * |
See also references of WO2009121715A1 * |
Also Published As
Publication number | Publication date |
---|---|
WO2009121715A1 (de) | 2009-10-08 |
US20110064585A1 (en) | 2011-03-17 |
US8360725B2 (en) | 2013-01-29 |
EP2265800B1 (de) | 2017-11-01 |
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