WO2010003725A1 - Turbinenschaufel für eine gasturbine und gusskern zum herstellen in einer solchen - Google Patents
Turbinenschaufel für eine gasturbine und gusskern zum herstellen in einer solchen Download PDFInfo
- Publication number
- WO2010003725A1 WO2010003725A1 PCT/EP2009/056074 EP2009056074W WO2010003725A1 WO 2010003725 A1 WO2010003725 A1 WO 2010003725A1 EP 2009056074 W EP2009056074 W EP 2009056074W WO 2010003725 A1 WO2010003725 A1 WO 2010003725A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- turbine blade
- openings
- casting core
- turbulence elements
- coolant
- Prior art date
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
- 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
- F05D2250/00—Geometry
- F05D2250/70—Shape
- F05D2250/71—Shape curved
- F05D2250/712—Shape curved concave
-
- 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
- F05D2260/2212—Improvement of heat transfer by creating turbulence
-
- 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 turbine blade for a gas turbine having a hollow, can be flowed around by a hot gas blade, at the trailing edge of which a plurality of openings for blowing a turbine blade cooling coolant are separated by interposed webs, wherein in the interior of the airfoil at least one with a plurality of the openings fluidically connected cavity is provided in the upstream of the webs several turbulence elements are provided, each having one of the incoming there coolant flow facing upstream side. Furthermore, the invention relates to a casting core for use in a casting apparatus for producing a cast turbine blade according to the preamble of claim 1 in order to leave behind a cavity traversed by a coolant in the turbine blade after removal of the casting core from the cast turbine blade.
- An initially mentioned turbine blade and a casting core for producing such a turbine blade are known, for example, from WO 2003/042503 A1.
- the known turbine blade has a cooled trailing edge at which a plurality of openings for blowing out the cooling air by interposed webs - which are also known in English as "tear drops" - are separated from each other.
- the arranged at the trailing edge of a common cavity is preceded by three rows of columnar sockets - in the English also known as "pin-fins" - are arranged, which increases the heat transfer of them passing cooling air and to increase the Pressure loss are provided there.
- the casting core required for producing such a turbine blade is shown in perspective in FIG. 7 of WO 2003/042503 A1.
- the space occupied by the casting core remains after production of the cast turbine blade as a cavity in the turbine blade, wherein in the casting core arranged openings is filled with casting material.
- the casting core represents the negative image of the interior of the turbine blade.
- the pin-fins known from WO 2003/042503 A1 have a cylindrical shape and connect the opposing inner surfaces of the suction side wall and pressure side wall of the blade of the turbine blade.
- EP 1 091 092 A2 discloses an air-cooled turbine blade.
- pins are arranged in the form of a grid in the cavity of the double wall.
- the pins have a diamond shape in principle, with their corners rounded and their edges are concave inward.
- a network of passages for cooling air each having a narrowed inlet and a narrowed outlet opening, between which a diffuser and nozzle section is arranged.
- the sections aim to slow down and accelerate the cooling air for efficient cooling.
- the object of the invention is therefore to provide an initially mentioned turbine blade for a gas turbine, which is efficient and sufficiently coolable with the smallest possible amount of coolant, and / or in which a casting core can be used in a casting device for the production, which is particularly robust to handle ,
- the object directed to the turbine blade is achieved with a turbine blade according to the features of claim 1.
- the task directed to the casting core is achieved with a casting core according to the features of claim 9.
- the invention is based on the finding that a more stable casting core can be achieved if the first openings arranged in the casting core trailing edge are further reduced in longitudinal section, so that the dividing webs arranged in the casting core widen.
- this widening of the dividing webs arranged in the casting core leads, in a turbine blade produced with such a cast core, to an enlargement of the openings arranged at the trailing edge, through which the coolant escapes from the turbine blade. Since previously these openings were also used to adjust the coolant consumption, enlarged openings thus lead to increased consumption of coolant. This increase is not desirable in principle and reduces the efficiency of the gas turbine.
- the invention proposes to increase the pressure loss in the area upstream of the trailing edge openings of the turbine blade, more precisely: in a cavity upstream of the openings, and thus to provide an increased flow resistance in order to achieve the aforementioned effect.
- the invention proposes that upstream of the webs a plurality of turbulence elements are provided each have one of the incoming there coolant flow facing upstream side, at least partially concave.
- Another advantage of the concaved upstream face of the turbulence elements is a further increase in the heat transfer between the inner surfaces of the airfoil side walls and the coolant flow therealong due to further increased turbulence in the coolant.
- the geometric dimensioning of the turbulence elements according to the invention is suitably selected to set the required internal pressure loss and / or the desired heat transfer.
- Pressure loss and heat transfer can also be adjusted by the appropriate choice of the number of turbulence elements according to the invention within a row transversely to the coolant main flow direction.
- the airfoil comprises a suction side wall and a pressure side wall, whose respective inner surfaces are the cavity and the laterally extending from the cavity to the openings extending channels between the webs.
- the turbulence elements each extend from one of the two inner surfaces to the other inner surface and connect them. Thus, coolant flow between the inner surface of the pressure side wall and the inner surface of the suction side wall is partially blocked.
- the two inner surfaces of the side walls may also be inclined relative to one another in such a way that they converge toward the trailing edge of the turbine blade, as viewed in the cross section of the blade.
- this makes it possible to present the minimum flow-through cross section of the turbine blade in a region in which the turbulence elements are arranged.
- This is a further difference from a turbine blade known from the prior art, in which there is usually the smallest cross-section through which the coolant can flow between the webs, which separates the openings or channels arranged in the trailing edge of the turbine blade.
- the turbulence elements are C-shaped viewed in longitudinal step. Their arc shape can consequently be circular segment-shaped or elliptical segment-shaped, ie sickle-like. Such a shape causes, if the ends are flown, a relatively large pressure loss.
- the bow ends of the turbulence elements are oriented such that they are at least slightly facing the incoming there in operation coolant flow.
- the coolant impinging on the concaved upstream side can be conducted and trapped from the two arcuate ends to the intermediate center, whereby a particularly large upstream of it Dynamic pressure in the coolant flow sets, which can lead to a particularly large pressure loss.
- a diversion of the cooling air should not be done with the turbulence elements according to the invention.
- the turbulence elements can be arranged directly upstream of the webs in at least one row transversely to the coolant main flow direction.
- each of the turbulence elements of the row preferably has an at least partially concavely curved inflow side. This makes it possible to set a uniform pressure loss for the coolant and a uniform heat transfer over the entire longitudinal extent of the turbine blade-in other words, over the entire height of the blade leaf.
- a turbine blade according to the invention viewed in the longitudinal direction of the blade leaf-the distance between two adjacent turbulence elements can be smaller by a factor of 2 than their respective extent in the longitudinal direction.
- a further means for intensifying the turbulence of the coolant flowing through the cavity to the openings can be provided.
- the further means may comprise a multiplicity of columns or sockets arranged in a grid, that is to say the cylindrical pin-fins known from the prior art.
- the further funds from at least one further series of inventive Mass turbulence elements is formed. Consequently, not only a single row of turbulence elements according to the invention may be present, but also a plurality of rows of turbulence elements according to the invention, which are each preferably aligned perpendicular to the coolant flow. This further increases the pressure loss.
- the cavities and outlet openings present in a cast turbine blade can be produced by a casting core used in a casting device, which is removed from the casting of the turbine blade in a known manner.
- a casting core is proposed for use in a casting apparatus, which comprises a casting core trailing edge on which a plurality of first openings for forming the webs are arranged in the trailing edge of the turbine blade.
- a plurality of second openings are provided in the casting core, which are arranged in a second region which is adjacent to a first region in which the first openings are arranged.
- the second openings of the casting core serve to produce the turbulence elements according to the invention.
- At least one of the second openings is at least partially concave-shaped.
- the concave part of the second openings of the casting core trailing edge is averted.
- a casting core designed in accordance with the invention therefore tends to break less near the casting core trailing edge than a conventional casting core and is accordingly simpler, more robust to handle.
- FIG. 2 shows a section analogous to FIG. 2 through a turbine blade according to the invention with concavely curved inflow sides according to a first embodiment
- FIG. 5 shows a casting core according to the invention in a perspective view for the production of an inventive
- FIG. 6 shows a cross section through the trailing edge of a turbine blade according to the invention.
- a gas turbine blade 10 relating to the invention is shown in perspective in FIG.
- the gas turbine blade 10 is designed according to FIG 1 as Laufschaufei.
- the invention can also be used in a guide vane, not shown, of a gas turbine.
- the turbine blade 10 comprises a cross-sectionally fir-tree-shaped blade root 12 and a platform 14 arranged thereon.
- the platform 14 is adjoined by an aerodynamically curved blade 16, which has a leading edge 18 and a trailing edge 20.
- Provided on the front edge 18 are cooling openings arranged as a so-called "shower head", from which a coolant flowing in the interior, preferably cooling air, can exit.
- the airfoil 16 comprises a - with respect to FIG 1 - rear suction side wall 22 and a front side pressure side wall 24.
- a plurality of trailing edge openings 28 are provided, which are seen by dazwi- arranged webs 30 separated from each other.
- Trailing edge 20 is designed as a so-called cut-back trailing edge, so that the openings 28 are rather on the pressure side than in the middle in the trailing edge 20th
- FIG. 2 shows the interior of the turbine blade 10 known from the prior art in a longitudinal section along a plane, spanned by a center line which extends from the front edge 18 to the trailing edge 20 of the blade 16, and the blade longitudinal direction, which extends from blade root 12th extends to the blade tip.
- the rear edge openings 28 are further arranged on the right, between which the webs 30 are arranged.
- the webs 30 extend substantially parallel to a hot gas flow which, during operation, flows around the airfoil 16 from the front edge 18 to the rear edge 20.
- Shown in FIG. 2 on the left is a multiplicity of column or pedestals 32 arranged in a grid. Both the columns 32 and the webs 30 extend from an inner surface 34 of the suction side wall 22 to an inner surface, not shown, of the pressure side wall 24. Consequently, the columns 32 are in a cavity 38 of the turbine blade 10, which is bounded laterally by the suction side wall 22 and the pressure side wall 24.
- a coolant preferably cooling air 40
- a coolant flows through the cavity 38 during operation.
- the part of the turbine blade which is not shown in FIG. 2, is formed in the interior in such a way that the field of bases 32 is substantially uniformly flowed through by cooling air 40.
- the uniform flow of the arranged in grid base 32 is shown by the arrows marked 40.
- the cooling air 40 impinges on individual pedestals 32 and is thereby deflected by them, the main flow direction 40 of which remains essentially unchanged. This creates 40 turbulences in the cooling air.
- the introduced from the hot gas in the blade walls 22, 24 heat is passed from these further into the base 32.
- the cooling air 40 impinging on the base 32 absorbs the heat and transports it. After the cooling air 40 has flowed through the base field, this enters channels 41, which connect the cavity 38 with the openings 28. After flowing through the channels 41, the cooling air 40 passes out of the turbine blade 10 through the openings 28 and mixes with the hot gas flowing around the blade 16.
- novel turbulence elements 42 are proposed with the invention according to FIG.
- the turbulence elements 42 according to FIG. 3 have an inflow side 44 facing the inflowing cooling air 40, which is concave at least partially curved.
- the turbulence elements 42 according to the invention are thus C-shaped, that is, they are sickle-shaped.
- each of the turbulence elements 42 of a row has an at least partially concavely curved upstream side 44 or is sickle-shaped.
- two rows of pin fins have been replaced by a series of turbulence elements 42 according to the invention.
- the sickle shape of the turbulence elements 42 can, as shown in FIG. 3 and FIG. 4, be aligned in the cavity 38 in such a way that the ends of a turbulence element 42 lie at different heights of the airfoil 16. Installed in a turbine these are then at different radii - relative to a machine axis of the gas turbine, around which the rotor rotates.
- the turbulence elements 42 are not only sickle-shaped in longitudinal section, but also crescent-shaped in cross-section. This results in a total cup or plate-shaped contour of the turbulence element 42 with an at least partially spherical inflow side 44, which generates a particularly large pressure loss.
- Cooling air occurs.
- the turbulence elements 42 have a further increased flow resistance compared to the sockets 32 arranged in rows, so that at this point an increased pressure loss occurs, which prevents the increase of coolant consumption.
- bulenzettin 42 to use in different rows.
- a length h in the longitudinal direction, a width b and thus the curvature of the concave upstream side 44 of the turbulence elements 42 and the distance L between two adjacent rows can be adapted to local requirements.
- FIG. 6 shows the section VI from FIG. 3 through a turbine blade according to the invention with the novel turbulence elements 42.
- the suction side wall 22 and the pressure side wall 24 extend to the trailing edge 20.
- the openings 28 are in turn separated from one another by webs 30 arranged therebetween.
- An inner surface 34 of the suction side wall 22 faces an inner surface 48 of the pressure side wall 24 in a wedge shape, so that viewed in the main flow direction of the coolant 40, these converge towards the trailing edge 20, i. converge.
- FIG. 5 shows a perspective view of a casting core 110 according to the invention with first openings 130 arranged in a first area near the casting core trailing edge 120.
- a plurality of second openings 142 arranged in two rows adjacent thereto in a second area are provided.
- the second openings 142 have at least one partial contour, which is concave-shaped.
- a turbine blade according to the invention can be produced therewith, wherein the space occupied by the casting core 110 remains as a cavity in the turbine blade after production of the cast turbine blade.
- the openings 130, 142 present in the casting core 110 are filled with cast material during the casting of the turbine blade 10 and remain Thus, subsequently as structural elements, namely as webs 30 and turbulence elements 42, in the turbine blade.
- a cast core 110 according to the invention has a complementary contour to the interior of the turbine blade according to the invention.
- the invention can be used in both a blade and a vane.
- the invention proposes a turbine blade with a partially new internal structure.
- the new elements are arranged upstream of the webs 30 arranged on the trailing edge 20 of the airfoil 16 of the turbine blade.
- the structure includes a series arranged turbulence elements 42, which has an inflowable by a coolant 40 upstream side 44, which according to the invention is at least partially concave curved.
- the turbulence elements 42 are formed sickle-shaped. This aerodynamically particularly unfavorable form of the turbulence elements 42 causes an increased pressure loss, which complicates the flow with coolant. This makes it possible to increase the width d of the openings 28 (compare FIG.
- the invention also provides a substantially more stable cast core 110, since the first openings 130 required for the production of the webs 30 of a turbine blade can now be spaced further apart than previously in the cast core 110. This leads to a greater stability of the casting core 110 in the region of the casting core trailing edge 120, whereby it tends to break less at this point and can therefore be handled more robustly.
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- 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
Description
Claims
Priority Applications (7)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
AT09793895T ATE549488T1 (de) | 2008-07-10 | 2009-05-19 | Turbinenschaufel für eine gasturbine und gusskern zum herstellen in einer solchen |
EP09793895A EP2304185B1 (de) | 2008-07-10 | 2009-05-19 | Turbinenschaufel für eine gasturbine und gusskern zum herstellen in einer solchen |
ES09793895T ES2381821T3 (es) | 2008-07-10 | 2009-05-19 | Pala de turbina para una turbina de gas y núcleo fundido para su fabricación |
US13/002,986 US20110176930A1 (en) | 2008-07-10 | 2009-05-19 | Turbine vane for a gas turbine and casting core for the production of such |
JP2011517050A JP5080688B2 (ja) | 2008-07-10 | 2009-05-19 | ガスタービンのためのタービンブレードまたはベーンならびにその内部の製造のための成型コア |
CN200980126714.4A CN102089498B (zh) | 2008-07-10 | 2009-05-19 | 用于燃气涡轮机的涡轮机叶片和用于制造这样的涡轮机叶片的型芯 |
PL09793895T PL2304185T3 (pl) | 2008-07-10 | 2009-05-19 | Łopatka turbiny do turbiny gazowej oraz rdzeń odlewniczy do produkcji takiej łopatki |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP08012518.0 | 2008-07-10 | ||
EP08012518A EP2143883A1 (de) | 2008-07-10 | 2008-07-10 | Turbinenschaufel und entsprechender Gusskern |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2010003725A1 true WO2010003725A1 (de) | 2010-01-14 |
Family
ID=39714166
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/EP2009/056074 WO2010003725A1 (de) | 2008-07-10 | 2009-05-19 | Turbinenschaufel für eine gasturbine und gusskern zum herstellen in einer solchen |
Country Status (8)
Country | Link |
---|---|
US (1) | US20110176930A1 (de) |
EP (2) | EP2143883A1 (de) |
JP (1) | JP5080688B2 (de) |
CN (1) | CN102089498B (de) |
AT (1) | ATE549488T1 (de) |
ES (1) | ES2381821T3 (de) |
PL (1) | PL2304185T3 (de) |
WO (1) | WO2010003725A1 (de) |
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EP2602439A1 (de) * | 2011-11-21 | 2013-06-12 | Siemens Aktiengesellschaft | Kühlbares Heißgasbauteil für eine Gasturbine |
US9366144B2 (en) | 2012-03-20 | 2016-06-14 | United Technologies Corporation | Trailing edge cooling |
FR2989608B1 (fr) * | 2012-04-24 | 2015-01-30 | Snecma | Procede d'usinage du bord de fuite d'une aube de turbomachine |
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EP4039388A1 (de) * | 2013-07-19 | 2022-08-10 | Raytheon Technologies Corporation | Generativ gefertigter kern |
EP2832955A1 (de) * | 2013-07-29 | 2015-02-04 | Siemens Aktiengesellschaft | Turbinenschaufel mit bogenförmigen zylindrischen Kühlkörpern |
US9551229B2 (en) | 2013-12-26 | 2017-01-24 | Siemens Aktiengesellschaft | Turbine airfoil with an internal cooling system having trip strips with reduced pressure drop |
WO2017082907A1 (en) * | 2015-11-12 | 2017-05-18 | Siemens Aktiengesellschaft | Turbine airfoil with a cooled trailing edge |
WO2017095438A1 (en) * | 2015-12-04 | 2017-06-08 | Siemens Aktiengesellschaft | Turbine airfoil with biased trailing edge cooling arrangement |
EP3417153A1 (de) | 2016-03-22 | 2018-12-26 | Siemens Aktiengesellschaft | Turbinenschaufel mit hinterkantenumrahmungsmerkmalen |
US20200003060A1 (en) * | 2017-01-18 | 2020-01-02 | Siemens Aktiengesellschaft | Turbine element for high pressure drop and heat transfer |
GB2559177A (en) * | 2017-01-30 | 2018-08-01 | Rolls Royce Plc | A component for a gas turbine engine |
WO2019005425A1 (en) | 2017-06-30 | 2019-01-03 | Siemens Aktiengesellschaft | AERODYNAMIC TURBINE PROFILE HAVING LEAK EDGE CHARACTERISTICS AND CASTING CORE |
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US7575414B2 (en) * | 2005-04-01 | 2009-08-18 | General Electric Company | Turbine nozzle with trailing edge convection and film cooling |
JP4872410B2 (ja) * | 2005-04-04 | 2012-02-08 | 株式会社日立製作所 | 内部に冷却通路を有する部材及びその冷却方法 |
US7980818B2 (en) * | 2005-04-04 | 2011-07-19 | Hitachi, Ltd. | Member having internal cooling passage |
US7513745B2 (en) * | 2006-03-24 | 2009-04-07 | United Technologies Corporation | Advanced turbulator arrangements for microcircuits |
US8177492B2 (en) * | 2008-03-04 | 2012-05-15 | United Technologies Corporation | Passage obstruction for improved inlet coolant filling |
US8506252B1 (en) * | 2010-10-21 | 2013-08-13 | Florida Turbine Technologies, Inc. | Turbine blade with multiple impingement cooling |
US8668453B2 (en) * | 2011-02-15 | 2014-03-11 | Siemens Energy, Inc. | Cooling system having reduced mass pin fins for components in a gas turbine engine |
-
2008
- 2008-07-10 EP EP08012518A patent/EP2143883A1/de not_active Withdrawn
-
2009
- 2009-05-19 AT AT09793895T patent/ATE549488T1/de active
- 2009-05-19 PL PL09793895T patent/PL2304185T3/pl unknown
- 2009-05-19 US US13/002,986 patent/US20110176930A1/en not_active Abandoned
- 2009-05-19 JP JP2011517050A patent/JP5080688B2/ja not_active Expired - Fee Related
- 2009-05-19 WO PCT/EP2009/056074 patent/WO2010003725A1/de active Application Filing
- 2009-05-19 ES ES09793895T patent/ES2381821T3/es active Active
- 2009-05-19 EP EP09793895A patent/EP2304185B1/de not_active Not-in-force
- 2009-05-19 CN CN200980126714.4A patent/CN102089498B/zh not_active Expired - Fee Related
Patent Citations (2)
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EP1091092A2 (de) * | 1999-10-05 | 2001-04-11 | United Technologies Corporation | Methode und Einrichtung zur Kühlung einer Wand in einer Gasturbine |
WO2003042503A1 (en) * | 2001-11-14 | 2003-05-22 | Honeywell International Inc. | Internal cooled gas turbine vane or blade |
Also Published As
Publication number | Publication date |
---|---|
PL2304185T3 (pl) | 2012-08-31 |
EP2143883A1 (de) | 2010-01-13 |
EP2304185A1 (de) | 2011-04-06 |
ATE549488T1 (de) | 2012-03-15 |
CN102089498A (zh) | 2011-06-08 |
JP5080688B2 (ja) | 2012-11-21 |
ES2381821T3 (es) | 2012-05-31 |
EP2304185B1 (de) | 2012-03-14 |
US20110176930A1 (en) | 2011-07-21 |
CN102089498B (zh) | 2014-01-01 |
JP2011527398A (ja) | 2011-10-27 |
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