EP2611990A1 - Turbinenschaufel für eine gasturbine - Google Patents
Turbinenschaufel für eine gasturbineInfo
- Publication number
- EP2611990A1 EP2611990A1 EP11749827.9A EP11749827A EP2611990A1 EP 2611990 A1 EP2611990 A1 EP 2611990A1 EP 11749827 A EP11749827 A EP 11749827A EP 2611990 A1 EP2611990 A1 EP 2611990A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- turbine blade
- side wall
- turbine
- elevations
- coolant
- 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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/12—Cooling
-
- 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
- F05D2250/10—Two-dimensional
- F05D2250/18—Two-dimensional patterned
- F05D2250/184—Two-dimensional patterned sinusoidal
-
- 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
- F05D2250/60—Structure; Surface texture
-
- 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
- F05D2260/202—Heat transfer, e.g. cooling by film 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
- 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 with a flow around a hot gas blade, which comprises a suction ⁇ sidewall and a pressure side wall extending in the flow direction of the hot gas from a common leading edge to a trailing edge, wherein at the trailing edge at least one opening for blowing a show ⁇ Felblatt previously cooling coolant is arranged, which is at least one opening with a angeordne ⁇ th in the blade cavity by means of a channel in flow communication, wherein the channel is also bounded by an inwardly facing surface of the suction side wall and an inwardly facing surface of the pressure side wall and a throttle element is provided for adjusting the amount of coolant emerging from the opening.
- 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 under the name "Pin-Fins" - are arranged, which increase 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 Cavity in the turbine blade, wherein in the casting core angeord ⁇ designated openings are filled with casting material.
- the casting core is the negative image of the inside of the door ⁇ binenschaufel.
- the pin-fins known from WO 2003/042503 AI have a cylindrical shape and connect the opposite inner surfaces of the suction side wall and pressure side wall of the blade of the 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. Between the pins thus creates 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.
- Cooling channels are designed zigzag through cast-in c-shaped ribs. This can be achieved a better cooling effect.
- the casting cores required for the production can be stiffened with it.
- 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.
- the turbine blade for a gas turbine comprises an airfoil which can be flowed around by a hot gas and which comprises a suction sidewall and a pressure sidewall which extend in the flow direction of the hot gas from a common leading edge to a trailing edge, at least one opening for blowing out a gas at or in the trailing edge the airfoil is previously arranged cooling coolant, which is at least one opening in fluid communication with a vane in ⁇ arranged cavity by means of a channel, wherein the channel also from an inwardly facing surface of the suction side wall and from an inwardly ge ⁇ facing surface of the pressure side wall is limited and to Ein ⁇ position of emerging from the opening amount of cooling air, a throttle element is provided, according to the invention, the throttle element upstream - in relation to the flow ⁇ direction of the channel - the respective opening is arranged and two surveys to summarized, which are each arranged on one of the two inwardly facing surfaces.
- the throttle element comprises at the inwardly facing surfaces arranged elevations which extend transversely to the flow direction of the channel and between which the minimum flow cross section of the channel is arranged ⁇ .
- the minimum vertical distance between each of the neutral fibers of the coolant flow and one of the two side surfaces in the cooling channel is to be detected.
- the throttle element is arranged in the upstream in the shop ⁇ felinneren the trailing edge opening.
- the throttle element is to be formed by two mutually related elevations, each of which are arranged on the inwardly facing surface of the suction side wall and pressure side wall. None of the elevations connects the suction side wall with the pressure side ⁇ wall.
- This disclosed embodiment of the throttle element is in particular ⁇ sondere A manufactured by casting turbine blades advantageous. As is known, turbine blades are usually produced in casting processes in which so-called lost casting cores are used to produce the internal cooling system. The production of these cores is usually done with the help of a core tool.
- the coring tool comprises two slide elements, which ⁇ can be moved towards or away from each other be. When pushed together, these slide elements surround a cavity which has the same contour as the cavity of the turbine blade to be cast.
- the casting core material is inserted into the cavity of the slider elements. After drying the casting core ⁇ materials of the casting core for producing the turbine blade is provided.
- the slide elements for the production of the first prototype According to the invention the turbine blade to be manufactured series designed so that in the interim to be manufactured turbine blade prototype of throttling, minimum distance In any case, the surveys are smaller than the theoretically required.
- the first turbine blade prototype thus prepared is then subjected to a coolant flow measurement. Desirably, due to the first time too small distance between the surveys, the throttle effect is too large, which initially leads to a low flow rate.
- the slide elements are changed. Their elevations are slightly changed, which increases in the collapsed state whose minimum distance. Subsequently, another casting core is produced with it. With this another turbine blade prototype is Herge ⁇ provides, the flow rate is then determined again and compared with the desired amount.
- each of the two slides can be processed by itself - such as by grinding the survey arranged thereon - without fundamentally changing the construction of the turbine blade and its cooling system. It is mög ⁇ lich that only one of the slide elements or both slide elements are processed during an iteration.
- the two elevations - seen in the flow direction of the cooling channel - offset from one another.
- the vertical distance between the inner surface of the pressure sidewall and the inner surface of the suction sidewall can be further reduced, resulting in particularly narrow trailing edge regions of airfoils. This reduces aerodynamic losses in hot gas flowing around the airfoil.
- elevation which is arranged on the inwardly facing surface of the pressure side wall, arranged downstream of that elevation, which is arranged on the inwardly facing surface of the suction side wall.
- This construction forces coolant flow in the channel, which flows more intensively past the inwardly facing surface of the suction sidewall.
- cut-back trailing edges an extended film cooling effect of the unprotected end of the suction-side trailing edge can be achieved, which reduces wear phenomena there and extends the service life of the turbine blade.
- Preferred dimensions plurality of openings are arranged at the trailing edge, wherein the cooling channel connects a plurality jointly Publ ⁇ voltages with the cavity.
- turbulence can also be generated during operation. zen be generated in the coolant. This turbulence can on the one hand contribute to the throttle effect and on the other hand to increase the heat transfer due turbulentererdemit ⁇ tel-flow.
- the interior of the turbine blade proposed by the invention can be used both for turbine blades with (for the side walls) common trailing edge and for turbine blades with a so-called cut-back trailing edge.
- FIG. 3 shows a cross section through the trailing edge region of a turbine blades according to the invention according to a first embodiment
- FIG. 4 shows a cross section through the trailing edge region of a turbine blades according to the invention according to a second embodiment.
- a gas turbine blade 10 relating to the invention is shown in perspective in FIG.
- the gas turbine blade 10 is formed according to FIG 1 as a rotor blade.
- the invention can also be used in a guide vane not shown 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 at the front edge 18 are cooling holes arranged as so-called "shower heads", from which a coolant flowing inside, preferably cooling air, can emerge.
- the airfoil 16 includes a - with respect to FIG 1 - rear suction side wall 22 and a front side ⁇ pressure side wall 24.
- the trailing edge 20 Along the trailing edge 20 a plurality of openings 28 are provided, which are separated by interposed webs 30 from each other.
- the trailing edge 20 is designed as a so-called cut-back trailing edge, so that the openings 28 are located on the pressure side rather than centrally in the trailing edge 20th
- FIG. 2 shows the interior of a loading from the prior art known turbine blade in a longitudinal section along a plane spanned by a center line, which it extends from the leading edge 18 to the trailing edge 20 of the airfoil 16 ⁇ , and from the blade longitudinally extending extends from the blade root 12 to the blade tip.
- the Hinterkantenöff ⁇ 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 blade blade 16 from the front edge 18 to the trailing edge 20.
- Shown in FIG. 2 on the left is a multiplicity of column or pedestals 32 arranged in a grid. Both the sockets 32 and the webs 30 extend from an inner surface 34 of the suction side wall 22 to an inner surface of the pressure side wall 24, not shown in FIG. 2. Consequently, the sockets 32 are arranged in a cavity 38 of the turbine blade 10, which is laterally separated from the suction side ⁇ tenwand 22 and the pressure side wall 24 is limited.
- the cavity 38 by a coolant such as cooling air 40 or cooling steam, flows through.
- a coolant such as cooling air 40 or cooling steam
- the part of the turbine blade 10, not shown in FIG. 2 is formed in the interior in such a way that the field of pedestals 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 strikes individual pedestal 32 and is thereby deflected by the latter, the main flow direction of which remains essentially unchanged. This creates 40 turbulences in the cooling air.
- the introduced from the hot gas in the show ⁇ feldress 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 into passages 41 which connect the cavity 38 with the openings 28. After flowing through the passages 41 the cooling air exits 40 through the openings 28 of the turbine blade 10 out and mixes with which the record ⁇ felblatt 16 flowing around the hot gas.
- elevations 42, 44 are provided on the inner surfaces 34, 36 of the suction side wall 22 or pressure side wall 24.
- One (42) of the two elevations 42, 44 is arranged on the inner surface 34 or part thereof, the other (44) of the two elevations 42, 44 is located on the inner surface 36 or part of this.
- the inner surfaces 34, 36 define a cavity 38 and a cooling channel 46, which connects the cavity 38 with the openings 28. It is pos ⁇ lich that cavity 38 and channel 46 merge into each other.
- the minimum distance between the inner surface 34 and the inner surface 36 in the region of the two elevations 42, 44 is now provided. For this purpose, in FIG.
- the minimum distance A forming the throttle element is located between the two elevations 42, 44, whereby they are in relation to one another.
- the elevations 42, 44 replace neither the base 32 nor the webs 30. According to FIG. 3, the elevations 42, 44 extend along the blade longitudinal direction (perpendicular to the plane of the page) over the entire height of the cooling channel 46.
- the contour of the elevations 42, 44 are As in the cross section shown in FIG 3, derge ⁇ stalt that they allow a continuous and edge-free course of the cooling channel in the flow direction of the coolant to the trailing edge opening 28 out. In this case, the cooling channel 46 converges.
- the cooling channel 46 may be provided that the
- Elevations are also designed in the form of ribs, as shown in FIG 4.
- the elevations 42, 44 have a rib-shaped contour with a height Hi or H 2 .
- the heights Hi and H 2 are comparatively large, so that a cooling air consumption can be determined which is below the desired or predetermined consumption.
- the core tool ie the ent ⁇ speaking slide elements are more prototypes gradu- ally produced which always consume slightly more coolant due to reduced rib heights Hi, H2 than the previously ge ⁇ manufactured prototype.
- Each iteration encompasses the herstel ⁇ len a turbine blade with a defined rib height Hi and H 2 and the determination of the coolant consumption of the corresponding turbine blade prototype.
- a cooling ⁇ agent consumption is determined corresponding to the desired or predetermined amount, the production of the sliding ⁇ berimplantation is completed, so that with the then available core Tool can be manufactured to an increased extent cores and thus turbine blades ⁇ with the desired coolant consumption, which significantly reduces the reject rate.
- a turbine blade 10 is specified, which allows a simple and cost-effective test phase during the phase of factory ⁇ production, to provide after completion of the iterations for a series of turbine blades 10 exactly crafted core tool.
- the casting cores required for casting the turbine blade 10 according to the invention break less frequently during handling than the casting cores known from the prior art.
- the throttle element comprises only a single elevation 44 (or 42) instead of two elevations 42, 44, so that the minimum distance between a single elevation 44 (or 42) and the opposite, then inwardly facing surface 34 (or 36) of suction side wall 22 (or pressure side wall 36) is located.
- the opposing surface 34 or 36 may then also be configured flat in the region of the minimum distance.
- a turbine blade 10 is given to ⁇ , the amount of out of the trailing edge 20 effluent coolant 40 is comparatively easily and accurately set immediately when casting the turbine blade 10 without reworking the cast turbine blade 10 in terms of setting the coolant consumption is necessary ,
- elevations 42, 44 are located on the inner surfaces 34, 36 of the suction side wall 22 and the pressure side wall 24, between which the throttle element is located, by means of which the quantity of outflowing coolant is adjusted.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
Claims
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP11749827.9A EP2611990B1 (de) | 2010-09-03 | 2011-08-29 | Turbinenschaufel für eine gasturbine |
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP10175235A EP2426317A1 (de) | 2010-09-03 | 2010-09-03 | Turbinenschaufel für eine Gasturbine |
PCT/EP2011/064811 WO2012028574A1 (de) | 2010-09-03 | 2011-08-29 | Turbinenschaufel für eine gasturbine |
EP11749827.9A EP2611990B1 (de) | 2010-09-03 | 2011-08-29 | Turbinenschaufel für eine gasturbine |
Publications (2)
Publication Number | Publication Date |
---|---|
EP2611990A1 true EP2611990A1 (de) | 2013-07-10 |
EP2611990B1 EP2611990B1 (de) | 2015-01-28 |
Family
ID=43545953
Family Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP10175235A Withdrawn EP2426317A1 (de) | 2010-09-03 | 2010-09-03 | Turbinenschaufel für eine Gasturbine |
EP11749827.9A Not-in-force EP2611990B1 (de) | 2010-09-03 | 2011-08-29 | Turbinenschaufel für eine gasturbine |
Family Applications Before (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP10175235A Withdrawn EP2426317A1 (de) | 2010-09-03 | 2010-09-03 | Turbinenschaufel für eine Gasturbine |
Country Status (5)
Country | Link |
---|---|
US (1) | US20130156599A1 (de) |
EP (2) | EP2426317A1 (de) |
JP (1) | JP5738996B2 (de) |
CN (1) | CN103080478B (de) |
WO (1) | WO2012028574A1 (de) |
Families Citing this family (14)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US9017026B2 (en) * | 2012-04-03 | 2015-04-28 | General Electric Company | Turbine airfoil trailing edge cooling slots |
US9145773B2 (en) * | 2012-05-09 | 2015-09-29 | General Electric Company | Asymmetrically shaped trailing edge cooling holes |
US8985949B2 (en) * | 2013-04-29 | 2015-03-24 | Siemens Aktiengesellschaft | Cooling system including wavy cooling chamber in a trailing edge portion of an airfoil assembly |
US9132476B2 (en) * | 2013-10-31 | 2015-09-15 | Siemens Aktiengesellschaft | Multi-wall gas turbine airfoil cast using a ceramic core formed with a fugitive insert and method of manufacturing same |
US10502066B2 (en) | 2015-05-08 | 2019-12-10 | United Technologies Corporation | Turbine engine component including an axially aligned skin core passage interrupted by a pedestal |
US10323524B2 (en) * | 2015-05-08 | 2019-06-18 | United Technologies Corporation | Axial skin core cooling passage for a turbine engine component |
EP3147455A1 (de) * | 2015-09-23 | 2017-03-29 | Siemens Aktiengesellschaft | Turbinenleitschaufel mit einer drosseleinrichtung |
US10260354B2 (en) * | 2016-02-12 | 2019-04-16 | General Electric Company | Airfoil trailing edge cooling |
EP3417153A1 (de) | 2016-03-22 | 2018-12-26 | Siemens Aktiengesellschaft | Turbinenschaufel mit hinterkantenumrahmungsmerkmalen |
KR20180082118A (ko) * | 2017-01-10 | 2018-07-18 | 두산중공업 주식회사 | 가스 터빈의 블레이드 또는 베인의 컷백 |
KR101875692B1 (ko) * | 2017-04-10 | 2018-07-06 | 연세대학교 산학협력단 | 가스터빈 냉각을 위한 직물형태의 내부 유로 구조를 포함하는 가스터빈 블레이드 |
WO2019005425A1 (en) * | 2017-06-30 | 2019-01-03 | Siemens Aktiengesellschaft | AERODYNAMIC TURBINE PROFILE HAVING LEAK EDGE CHARACTERISTICS AND CASTING CORE |
EP3492700A1 (de) * | 2017-11-29 | 2019-06-05 | Siemens Aktiengesellschaft | Innengekühlte turbomaschinenkomponente |
US10753210B2 (en) * | 2018-05-02 | 2020-08-25 | Raytheon Technologies Corporation | Airfoil having improved cooling scheme |
Family Cites Families (14)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5356265A (en) * | 1992-08-25 | 1994-10-18 | General Electric Company | Chordally bifurcated turbine blade |
JP3651490B2 (ja) * | 1993-12-28 | 2005-05-25 | 株式会社東芝 | タービン冷却翼 |
JPH08334003A (ja) * | 1995-06-06 | 1996-12-17 | Mitsubishi Heavy Ind Ltd | 冷却翼後縁冷却装置 |
US5752801A (en) * | 1997-02-20 | 1998-05-19 | Westinghouse Electric Corporation | Apparatus for cooling a gas turbine airfoil and method of making same |
EP1046784B1 (de) * | 1999-04-21 | 2004-08-11 | ALSTOM Technology Ltd | Kühlbares Bauteil |
US6402470B1 (en) | 1999-10-05 | 2002-06-11 | United Technologies Corporation | Method and apparatus for cooling a wall within a gas turbine engine |
DE50106385D1 (de) * | 2001-03-26 | 2005-07-07 | Siemens Ag | Verfahren zur Herstellung einer Turbinenschaufel |
US6974308B2 (en) | 2001-11-14 | 2005-12-13 | Honeywell International, Inc. | High effectiveness cooled turbine vane or blade |
US6607356B2 (en) * | 2002-01-11 | 2003-08-19 | General Electric Company | Crossover cooled airfoil trailing edge |
EP1653046A1 (de) * | 2004-10-26 | 2006-05-03 | Siemens Aktiengesellschaft | Gekühlte Turbinenschaufel sowie Verfahren zur Einstellung des Durchflussvolumens eines Kühlmediums |
US7575414B2 (en) * | 2005-04-01 | 2009-08-18 | General Electric Company | Turbine nozzle with trailing edge convection and film cooling |
US7780415B2 (en) * | 2007-02-15 | 2010-08-24 | Siemens Energy, Inc. | Turbine blade having a convergent cavity cooling system for a trailing edge |
US7785070B2 (en) * | 2007-03-27 | 2010-08-31 | Siemens Energy, Inc. | Wavy flow cooling concept for turbine airfoils |
CH700321A1 (de) * | 2009-01-30 | 2010-07-30 | Alstom Technology Ltd | Gekühlte schaufel für eine gasturbine. |
-
2010
- 2010-09-03 EP EP10175235A patent/EP2426317A1/de not_active Withdrawn
-
2011
- 2011-08-29 JP JP2013526429A patent/JP5738996B2/ja not_active Expired - Fee Related
- 2011-08-29 WO PCT/EP2011/064811 patent/WO2012028574A1/de active Application Filing
- 2011-08-29 EP EP11749827.9A patent/EP2611990B1/de not_active Not-in-force
- 2011-08-29 CN CN201180042590.9A patent/CN103080478B/zh not_active Expired - Fee Related
- 2011-08-29 US US13/818,794 patent/US20130156599A1/en not_active Abandoned
Non-Patent Citations (1)
Title |
---|
See references of WO2012028574A1 * |
Also Published As
Publication number | Publication date |
---|---|
EP2426317A1 (de) | 2012-03-07 |
WO2012028574A1 (de) | 2012-03-08 |
JP2013536913A (ja) | 2013-09-26 |
JP5738996B2 (ja) | 2015-06-24 |
CN103080478A (zh) | 2013-05-01 |
CN103080478B (zh) | 2015-05-20 |
US20130156599A1 (en) | 2013-06-20 |
EP2611990B1 (de) | 2015-01-28 |
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